ii TABLE OF CONTENTS FACT SHEET: MARS NETLANDER MISSION OF OPPORTUNITY ...... v

SCIENCE INVESTIGATION...... 1

THE CASE FOR MARS NETWORK SCIENCE...... 1 THE NETLANDER MISSION ...... 2 OUR ROLE IN THE NETLANDER MISSION...... 2 NetLander PSP/DAP Program ...... 3 SEIS: SCIENCE GOALS AND OBJECTIVES ...... 4 Baseline Mission and Descope Options...... 6 SEIS: SCIENCE IMPLEMENTATION...... 7 SEIS: Instrumentation...... 7 SEIS: Mission Description...... 9 SEIS: Data Analysis and Archiving ...... 10 SEIS: Science Team ...... 10 NEIGE: SCIENCE GOALS AND OBJECTIVES...... 12 Baseline Mission and Descope Options...... 14 NEIGE: SCIENCE IMPLEMENTATION...... 14 NEIGE: Instrumentation...... 14 NEIGE: Mission Description...... 15 NEIGE: Data Analysis and Archiving ...... 17 NEIGE: Science Team ...... 17 ATMIS: SCIENCE GOALS AND OBJECTIVES ...... 19 Baseline Mission and Descope Options...... 21 ATMIS: SCIENCE IMPLEMENTATION ...... 21 ATMIS: Instrumentation ...... 21 ATMIS: Mission Description ...... 23 ATMIS: Data Acquisition, Analysis and Archiving ...... 23 ATMIS: Science Team...... 25 EDUCATION/PUBLIC OUTREACH ...... 26

NETLANDER PROJECT OVERVIEW ...... 26 NETLANDER OUTREACH ABSTRACT ...... 26 ROLES AND RESPONSIBILITIES...... 26 NETLANDER OUTREACH PROGRAM ADDRESSES DISCOVERY E/PO GOALS ...... 27 NEW TECHNOLOGY TRANSFER...... 30

SMALL DISADVANTAGED BUSINESS PLAN ...... 31

MISSION IMPLEMENTATION...... 32

MISSION PROGRAMMATIC DESCRIPTION...... 32 NetLander DataPolicy ...... 32 Safety and Mission Assurance...... 33 SEIS: GENERAL MISSION INFORMATION...... 34 SEIS: Characteristics and Fabrication...... 34 SEIS: Resources and Margins...... 36 SEIS: Interfaces...... 36 NEIGE: GENERAL MISSION INFORMATION...... 37 NEIGE Instrumentation on the Orbiter ...... 37 NEIGE: Orbiter Interface ...... 37 NEIGE Uplink/Downlink Requirements ...... 39 NEIGE Resources and Margins...... 39 ATMIS: GENERAL MISSION INFORMATION: ...... 40

iii ATMIS Instrument Characteristics ...... 40 ATMIS: NetLander Interface, Resources and Margins ...... 40 ATMIS: Lander Attitude Requirements...... 42 MANAGEMENT AND SCHEDULE ...... 43

COST AND COST ESTIMATING METHODOLOGY...... 49 Cost Estimating Methodology...... 49 Reserve Strategy...... 49 Science Cost Details...... 49 Instrument Development Cost Details ...... 49 Table B2: NASA OSS COST FUNDING PROFILE TEMPLATE FOR MISSIONS OF OPPORTUNITY ...... 52 Table B3: MISSION PHASE SUMMARY OF NASA OSS COST...... 53 APPENDIX 1: STATEMENT OF WORK ...... 54

APPENDIX 2: LETTERS OF ENDORSEMENT...... 55

APPENDIX 2B: E/PO LETTERS OF ENDORSEMENT...... 64

APPENDIX 3: RESUMES...... 75

APPENDIX 4: COMPLIANCE WITH U.S. EXPORT LAWS AND REGULATIONS ...... 102

APPENDIX 5: OUTLINE OF TECHNICAL RESPONSIBILITIES BETWEEN U.S. AND INTERNATIONAL PARTNERS ...... 103

APPENDIX 6: COMPLIANCE WITH PROCUREMENT REGULATIONS BY NASA PI PROPOSALS ..104

APPENDIX 7: ACRONYMS LIST...... 105

APPENDIX 8: REFERENCES ...... 107

iv FACT SHEET: Mars NetLander Mission of Opportunity The NetLander Mission will offer the first opportunity to perform Network Science on Mars. This proposal requests NASA support for US hardware contributions to, and science participation in, three NetLander experiments previously selected through a European AO: SEIS (seismic network), ATMIS (meteorological network), and NEIGE (radio geodesy). These contributions are vital for each of these investigations to achieve its science goals. The simultaneous, long-term, continuous monitoring of seismic activity, atmospheric behavior, and geodetic parameters from this network of stations will answer fundamental questions about Mars’ internal structure and global climate. These goals are central to addressing NASA Space Science Themes and will provide much of the basic foundation for understanding the role and evolution of water on the surface of Mars. In addition, through the proposed PSP/DAP programs, other U.S. scientists will be able to take advantage of the wealth of scientific data generated by the NetLander mission. NetLander Mission Overview Four NetLanders will be built by the NetLander Consortium, under the leadership of CNES. The landers will be integrated onto a CNES communications orbiter and launched aboard an Ariane 5 in 2005. Three NetLander experiments include US components proposed here. The SEIS seismic experiment and the ATMIS meteorological experiment will be integrated into each lander. The NEIGE geodesy experiment will provide hardware on the orbiter. The four landers will be targeted to their intended landing sites and released on Mars approach. Atmospheric structure measurements will be made as they traverse the atmosphere on their way to the surface. Each lander will use a Mars-Pathfinder-style airbag landing system. After landing, each NetLander will deploy its solar panels, communications antenna, and scientific experiments. The landers and orbiter will collect atmospheric, seismic, and geodetic data for a full Martian year, comprising the first measurements from a science network on Mars.

NetLander Investigation Goals Address NASA Space Science Themes Theme: Understand the constitution and fundamental processes of the planets. · Determine the internal structure and dynamics of Mars in terms of the SEIS composition, mineralogy, and thermal state · Determine the level and distribution of current volcano-tectonic activity, and the current meteoroid flux at Mars Theme: Understand the constitution and fundamental processes of the planets. Theme: Understand interactions between the atmosphere and surface NEIGE · Determine the internal structure of Mars in terms of core and mantle radii, mineralogy, and thermal state. · Determine the seasonal changes in the polar ice cap mass distribution. Theme: Understand the current weather and climate on Mars Theme: Understand interactions between the atmosphere and surface ATMIS · Acquire coordinated meteorological measurements from a network of 4 sites to characterize the processes that maintain the thermal structure and dynamics of the Martian atmosphere. v Education/Public Outreach The NetLander Project E/PO effort has direct involvement by science team members with extensive previous E/PO experience. Our E/PO efforts will focus on pairing educators with science team members to develop exciting and engaging educational materials which meet the needs of students while adhering to national and state standards for excellence. Management U.S. contributions to NetLander One of four landers is shown. US A consortium of international agencies is contributions include short period implementing the mission, with CNES taking seismometers, temperature and wind overall management responsibility. The US instruments will be managed by JPL. Each of velocity sensors, and dual-frequency Doppler measurements for geodesy (on the experiments proposed here will have a Co-I orbiter). Other instruments on the with responsibility for that investigation; the PI landers (not in this proposal) include for this proposal, Bruce Banerdt, will represent the U.S. science interests to the NetLander ground-penetrating radar, an electric field experiment, a magnetometer, and Steering Group. Participating in this mission in a panoramic stereo camera. partnership with the European NetLander Consortium represents an opportunity for Schedule and Cost excellent science at significant cost savings. The NetLander Mission will be launched in Cost Summary (Thousands of FY01$) 2005 on an Ariane 5. US-contributed hardware will be developed and delivered in the 2001- Man. SEIS NEIGE ATMIS Phase A/B: 810 700 1835 1572 2004 timeframe, with operations, science Phase C/D: 1403 2039 8876 4132 analysis and E/PO activities continuing through Phase E: 331 1636 2065 2107 2008. Ample cost reserves (20-30%), as well Cost before reserves $27506 as schedule (>1 mo/yr, funded) and technical Instrument Reserves $3637 (30%) (mass and power ~20%) reserves are available Man./Sci. Reserves $3320 (20%) to cover development and interface Total MissionCost: $34463 contingencies. NetLander Investigation Schedule

The NetLander Mission represents the first opportunity for network science on Mars, emphasizing global, long-term, continuous monitoring of seismicity, rotational dynamics, and climate. By sharing expenses with our European partners, we maximize our science return for a small investment. ATMIS and NEIGE have flight heritage which minimizes their technical risk, and all three exploit the unique capabilities of a surface network to apply new technologies to address fundamental goals – not just monitoring the seismic activity and weather of Mars, but providing a 3-dimensional view of the interior based on seismic analysis, geodetic constraints on the deep internal structure and seasonal atmospheric behavior, and the first chance to study atmospheric circulation and surface-atmosphere interactions simultaneously at multiple points on Mars. This global view will revolutionize our understanding of the structure, dynamics and evolution of Mars.

vi SCIENCE INVESTIGATION information, when combined with the seismic The Case for Mars Network Science and geodetic constraints on the internal The NetLander Mission provides the first structure, will provide the foundation for opportunity to acquire coordinated seismic, studies of the roles and history of volatiles, geodetic, and meteorological observations from particularly water, on Mars. a network of stations on Mars. These Here, we propose to contribute to three investigations will provide important new Mars NetLander investigations: constraints on the structure, composition, and · Seismology (SEIS) processes of the interior of Mars as well as the · Geodesy (NEIGE), and atmospheric structure and near-surface weather · Meteorology (ATMIS) and climate (Fig. 1). This Mission of These 3 experiments will directly address the Opportunity Proposal requests NASA funding issues described above by obtaining for the U.S. instrument and Science Team simultaneous measurements on Mars from a contributions to the NetLander Mission. network of four small, capable, long-lived The data to be collected by this mission are landers. fundamental to our understanding the origin, These investigations relate directly to evolution, and present state of the planet Mars. recommendations by NASA planetary science This includes characterization of the core, advisory groups. For example, the report titled mantle, and crust in terms of depth of “An Integrated Strategy for Planetary Sciences boundaries, composition, and mineralogy (e.g., 1995-2010” from the Committee on Planetary phase transitions in the mantle), and and Lunar Exploration of the National determination of the thermal history and state, Research Council (COMPLEX, 1995) as well as the closely associated tectonic and identified two main themes to guide planetary volcanic history of Mars. In addition, this science in the next two decades: understanding proposal addresses the behavior of the climate planetary origins and understanding the and general circulation of the atmosphere and constitution and fundamental processes of the its interactions with the solid surface. This planets themselves. Within this latter theme planetary surfaces/interiors and atmospheric structure/processes comprised two of the four major components. The report proposed several specific goals related to these themes, five of which will be directly addressed by this mission: • “Understand the internal structure and dynamics of at least one solid body, other than the Earth or the Moon...” • “Specify the nature and sources of stress that are responsible for the global tectonics of Mars,

Venus, and several icy satellites of the outer L planets.” • “Advance significantly our understanding of Fig. 1: Whereas the surface of Mars has crust–mantle structure for all the solid planets.” been the subject of a decades–long program • “Understand Mars' inventory of volatiles and of exploration, only the proposed seismic its evolution and how these relate to historical and geodesy investigations can explore the climate changes.” vast interior of Mars which is otherwise • “Specify the processes that control inaccessible to observation. In addition (atmospheric) dynamics on … Mars …” atmospheric observations by a network of COMPLEX (1995) also states “The primary landers will provide the first large-scale objectives of atmospheric sciences and monitoring of Martian meteorology (based geophysics [on Mars] will require both long- on a figure © Calvin J. Hamilton). term global surveillance and the deployment of

NetLander Mars Science Network 1 a network of long-lived monitoring stations”. More recently, the Planetary Roadmap Development Team (1996) suggested a "Mars Network" as a campaign which responds to the quests which fundamentally motivate the planetary exploration program. The proposed experiments on the NetLander mission directly address all of the fundamental objectives envisioned for the Mars Network Campaign.

The NetLander Mission Fig. 2: Proposed locations for the four The NetLander Mission is the first NetLanders on Mars. Three are clustered planetary mission to focus on the interior of the near the Tharsis Bulge where most seismic planet and the large-scale circulation of the activity is expected, and one lander is atmosphere. This mission will deploy four located antipodal to the other three to help landers on Mars, establishing a network of resolve deep internal structure. science stations (Fig. 2). Each lander will study In spite of the high priority of the network the subsurface, interior, atmosphere, science objectives enabled by the NetLanders, ionospheric structure, and geodesy of Mars. funds to support the U.S. contributions to the A consortium of international agencies will ATMIS, SEIS, and NEIGE experiments were implement the mission. This project is not available from the Mars Exploration managed by the Centre National d'Etudes Program because the NetLanders did not Spatiales (CNES) of France, which accords it directly support the Mars Sample Return the highest priority within the Mars Exploration mission. Instead, NASA Headquarters Program. The other major players are instructed the US Co-I’s to submit a Discovery Ilmatieteen Laitos (Finnish Meteorological Mission of Opportunity proposal to obtain an Institute, FMI), and Deutschen Zentrum für evaluation by a NASA peer-review process. In Luft und Raumfahrt (German Space Agency, addition, it was specifically requested that all DLR). CNES has also had extensive U.S. science contributions for NetLander be discussions with NASA about collaboration in included in a single proposal, with the this project. investigations kept sufficiently distinct that Although the International Mars they could be evaluated (and selected) Exploration Program plans are currently independently. The result is this proposal, in evolving rapidly, we were told by CNES that which we describe crucial hardware for the purposes of this proposal we should contributions and science participation in three assume that the NetLander Mission would be distinct, independent NetLander experiments. launched in 2005 on an Ariane 5, with a CNES communications orbiter. Several days prior to arrival at Mars, the landers will be separated Our Role in the NetLander Mission from the carrier spacecraft and targeted to This proposal requests support for U.S. locations on the Martian surface. During the contributions to three experiments on the baseline mission of one Martian year, the European NetLander Mission to Mars (Fig. 3): payloads will conduct simultaneous the NetLander Seismometer (SEIS), the seismological, electromagnetic, atmospheric, NetLander Geodesy Experiment (NEIGE), and ionospheric, and geodetic measurements, as the Atmospheric and Meteorological well as ground penetrating radar sounding and Instrumentation System (ATMIS). panoramic imaging. These data will be The goal of the NetLander seismic combined with simultaneous observations from investigation is to reveal the structure and the planned Mars Express Orbiter. processes of the interior of Mars for the first NetLander: First network of science stations on Mars enables a new, in-depth study of Martian climate and internal structure, providing innovative science at a fraction the cost of a full mission.

NetLander Mars Science Network 2 time. To meet these goals, the seismic density structure as the probes descend through experiment must have ultra-broad-band (UBB) the atmosphere of Mars and will measure the seismometers with high-volume telemetry weather and climate at the surface for up to one (Solomon et al., 1991; Banerdt et al., 1996). Martian year. To do this each lander carries The seismic instrumentation must be able to instruments to measure the atmospheric measure extremely small seismic disturbances pressure, soil and atmospheric temperature, over a wide range of wavelengths spanning wind velocity, humidity, and airborne dust solid body tides, normal modes, surface waves, abundance. We will provide the atmospheric and high-frequency body waves. We will temperature and wind velocity sensors. The supply the sensors which will provide the atmospheric science experiment is led by the middle to high frequency response (0.1-50 Hz) Finnish Meteorological Institute and includes of the seismometer instrument, while the contributions from the U.K., Denmark, and Institute de Physique du Globe in Paris will France. supply the lower frequency range sensor, and More detailed descriptions of the scientific the Swiss will provide electronics. goals of these instruments as well as their The goal of the NetLander geodesy individual implementation plans and costs are investigation is to determine the rotational described in later sections in this proposal. irregularities of the planet including precision measurements of precession, nutation, length of NetLander PSP/DAP Program day variations, and polar motion. This will The Mars NetLander Science Team provide important and complementary strongly supports NetLander Participating information on the interior of Mars including Scientist and Data Analysis Programs to constraints on interior structure, temperature, encourage U.S. participation in this and future and composition, and estimates of the size and international Mars missions. We suggest that density of a fluid core. The geodesy NASA support a PS program that includes at experiment will also place constraints on the least one full time equivalent (FTE) for each of seasonal sublimation/condensation of the ice the 8 NetLander experiments identified in Fig. caps. This experiment involves the precision 3. If this program were initiated at the measurement of Doppler shifts between the beginning of the Operations phase, and lasted 3 orbiter and the landers. We will provide the years (FY06 - FY08) its total cost would be orbiter portion of this radio instrumentation approximately $4.5M. Furthermore, to ensure while CNES will provide the lander portion. that this global data set is fully analyzed, we The goal of the meteorological recommend a similar amount for a investigation is to make multiple, coordinated complementary Data Analysis Program after measurements from a network of four stations. the end of the primary mission. This experiment will record the atmospheric

Fig. 3: NetLander instrument layout, showing placement of instruments in lander. Four landers will be deployed to Mars (orbiter components of NEIGE not shown). They will develop the first Martian science network, enabling the first studies of the Martian interior and global climate. This proposal requests NASA support for US contributions to ATMIS, SEIS, and NEIGE.

NetLander Mars Science Network 3 Table 1. Objectives of SEIS address fundamental questions of planetary structure and evolution. SEIS: Science Goals and Objectives generated that will almost certainly be released Space Science Theme Understand the constitution and fundamental processes of the planets. through quakes, as on the Moon. The rate of Science Objectives thermal stress generation depends on the Determine the internal structure and dynamics of Mars in terms of its composition, The goal of the NetLander seismic cooling rate of the planet, which has been mineralogy, and thermal state. investigation (SEIS) is to peer through the estimated from thermal history calculations to Investigation Goals be about 50 K per billion years. Using Determine the level and distribution of Mars’ current volcano-tectonic activity, and surface layers of Mars and reveal the structure the current meteoroid flux at Mars. and processes of its interior in order to address representative values of the compressive some of the most fundamental questions about strength and thermal expansivity of rock, a 1. Determine the level and distribution of seismic activity: the planet. Table 1 shows the flow down from stress generation rate of about 250 GPa per · Use body wave arrivals at multiple stations to determine the location, origin time, the top–level space science theme, to the goals million years is derived. Together with and size of seismic events. we set for our investigation, and finally to the empirical data that relate stress generation rate · Investigate the correlation of contemporary seismicity with the recorded effects of specific science objectives for this experiment. to the rate of quake occurrence at a given past tectonics as manifested by structures observed on the surface. In order to fully address all of these magnitude level, Phillips (in Solomon et al., · Investigate the correlation of seismicity with regions for which large stresses are objectives, a network of extremely sensitive, 1991) estimated a level of activity inferred from geophysical studies. ultra-broad-band (UBB) seismometers with corresponding to 1 Mars quake of magnitude 5 · Determine the sources of stress responsible for the seismic activity. high-volume telemetry is required (Solomon et per Mars year, 10 of magnitude 4, and 100 of Science Objectives · Infer the current meteoroid flux at Mars. al., 1991; Banerdt et al., 1996). Such magnitude 3 (magnitude refers to the terrestrial 2. Determine the deep internal structure of the planet, including: instrumentation (Table 2) must be able to body wave magnitude for an equivalent seismic · Develop travel time versus distance curves for prominent seismic phases, and measure extremely small seismic disturbances moment). This activity is about 100 times invert them for seismic velocity as a function of depth. over a wide range of wavelengths spanning greater than shallow moonquake activity · Infer the thickness and physical properties of the Martian crust. solid body tides, normal modes, surface waves, (though still 100–1000 times lower than the · Infer the structure and seismic transmission properties of the mantle. and high-frequency body waves. Ground Earth). · Infer the size, and physical state of the core. coupling, thermal control, and isolation from A similar level of Martian seismic activity · Estimate the seismic attenuation of the interior and infer its thermodynamic both the lander and environmental noise must (a factor of two higher) was derived by structure. be carefully addressed for a sensitive UBB Golombek et al. (1992), who estimated the seismometer (Lognonné et al., 1996). The seismicity based on a time extrapolation of the Table 2: SEIS Subsystems NetLander Seismometer (SEIS) experiment historical slip apparent on faults visible at the Sub-System Supplier Heritage satisfies these requirements. A block diagram surface of Mars today. This estimate was Short Period Sensors JPL JPL Microseismometer Development, PIDDP, Rosetta Lander of the SEIS instrument is shown in Fig. 4. calibrated with a similar calculation for the (this proposal) USA Moon. Long Period Sensors IPGP Mars ’96 OPTIMISM Investigation Approach In addition to internal sources, seismic France Virtually nothing is known about the events will be caused by meteorite impacts. SEIS Electronics ETH Mars ’96 OPTIMISM seismic character of Mars, apart from a loose This is potentially a significant source of Switzerland. statistical upper bound on the rate of seismicity activity, as can be seen from experience with determined from the absence of seismic events the lunar seismic network which recorded 1743 detected by the Viking II seismometer (Goins clearly identified impact events on the LP and Lazarewicz, 1979; Solomon et al., 1991; instrument (Nakamura et al., 1982) and several Lognonné and Mosser, 1991). Thus one of the times that many on the SP (Duennebier and first objectives of the proposed seismic Sutton, 1974). Eighteen of these events were investigation will be to determine the large enough to be useful for internal structure seismicity and the noise floor. Seismicity, or studies. Most of the events detected on the the frequency of occurrence of quakes as a Moon were caused by objects between 1 and function of size and location, is a basic 1000 kg in mass, large enough to penetrate the quantity, which gives direct information on the Martian atmosphere (Gault and Baldwin, tectonic and volcanic activity of the planet. It 1970). Nakamura (in Solomon et al., 1991) has also determines the feasibility of passive estimated the expected rate of impact– seismic investigations of the planet’s interior. generated seismic activity on Mars, accounting Seismic Activity. There is little evidence for the different orbital location in the solar that the rigid lithosphere of Mars is broken up system, gravity, size, and atmosphere of Mars. into individual plates that move relative to each He concludes that the detection rate should be other. Thus plate tectonics, the dominant only slightly smaller on Mars than the Moon mechanism for generating quakes on the Earth for the larger impact events, although it should Fig. 4: Block diagram of SEIS showing European contributions with U.S.-provided components is missing. However, the lithosphere contracts be considerably smaller for the small impacts. in orange. Command/data lines in blue. as the planet cools and thermal stresses are

Netlander SEIS: Mars Seismic Network 4 As a lower quantitative bound, he estimates measure the ground motion expected for about one event per year with an equivalent Martian quakes. magnitude 2.5 and 20 with a magnitude 2.0. Recently, Moquet (1999) calculated the Based on plausible ranges of uncertainties, expected amplitudes of seismic waves on Mars actual rates may be 10–100 times higher. using a number of reasonable assumptions for Signal and Noise Characteristics. Knowing attenuation and gross structure. His calculations the characteristics of seismic signals on a planet account for crustal transmission, internal is vitally important for identifying the refraction, geometrical spreading, and occurrence of quakes in the seismic record, i.e., attenuation, as well as the corner frequency of differentiating them from noise. In addition, it the source. Fig. 5 shows the acceleration can give direct information about the properties amplitude spectrum for P and S waves from a of the medium through which the wave has quake of seismic moment 1015 Nm. For traveled. For example, on the Moon the gradual reference, this corresponds to an energy release build–up and long duration of signals (relative equivalent to a magnitude 4 quake on the Earth. to terrestrial signals) were indications of a high Golombek et al. (1992) predicted that such Q and intense scattering in the crust. Inherent in events should occur on average about every 25 the signal is the more detailed information, days on Mars. which allows the investigation of the planet’s Fig. 5 shows that a quake of this size will internal structure. produce waves with an acceleration amplitude The character of seismic noise will of well over 10-8 m/sec2 virtually everywhere on determine the detectability of small events. the planet (excluding shadow zones produced by Because the number of quakes should increase the core). The SEIS SP seismometer is designed geometrically with decreasing size, the lower to have a noise density floor of about 5 x 10-9 bound of detectability plays a crucial role in m/sec2 over the frequency range of 0.1 to 10 Hz, seismic analysis. The dominant component of giving a rms noise amplitude of 1-2x10-8 m/sec2 seismic noise on the Earth is due to the oceans; (depending on the bandwidth). This is well on the Moon it is primarily thermal cracking of within the maximum frequency band and surface rocks, at a level more than three orders amplitude range for detecting these events. By of magnitude lower than the Earth. Mars, with comparison, the Viking seismometer would its tenuous atmosphere and lack of open bodies have been extremely fortunate to detect such a of water, may not be like either of these. quake. Using the rate estimates of Golombek et Results from the Viking Lander seismic al. (1992), we expect to detect about 25 events experiment (Anderson et al., 1977) suggest that wind will play a major role in the generation of seismic noise, although that instrument's Viking location on the spacecraft exacerbated this effect. To mitigate these problems, the NetLander SEIS will be deployed directly on

the surface, and decoupled from the NetLander 2

body in a structure designed to attenuate wind m/s noise and temperature-induced variations in the seismic record. A recent analysis by Lognonné et al. (1996) suggests that the inherent level of seismic noise on Mars (in the absence of SEIS SP lander-induced noise) should be substantially below that of the Earth. Detectability of Seismic Events. The ability Fig. 5: Ground disturbance vs. frequency for to detect seismic events is key to the success of a quake of seismic moment 10-15 Nm (from any seismic investigation. Unfortunately, the Moquet, 1999). Each curve corresponds to a sensitivity of the Viking seismometer was so different distance in degrees (1° is about 60 low as to provide little useful information km on Mars). The thin line denotes sensitivity (Anderson et al., 1977). Thus it is imperative to of the Viking seismometer, and the thick line send an instrument with sufficient sensitivity to is the sensitivity of the SEIS SP seismometer.

Netlander SEIS: Mars Seismic Network 5 of this size over the course of our nominal presence of a layer of liquid or frozen water. mission (1 Mars year). If we are successful in Seismograms can be used to retrieve the locating our stations in regions with higher than receiver function that characterizes the response average activity, this number could easily of the layering beneath the station on the scale increase by an order of magnitude due to the of hundreds of meters. The receiver function can geometrically greater numbers of smaller but be computed from simple deconvolution of closer events which can provide detailed horizontal teleseismic records by the information on the crust and upper mantle. corresponding vertical records (Helmberger and Interior structure from body-wave Wiggins, 1971). This simple technique has been seismology. The fundamental measurement of used successfully on data with a range of quality seismology is the time series of ground motion (see, e.g., Langston, 1981). From the receiver at a point on the surface of the planet induced function, a layered model can be estimated using by the elastic waves radiated from a seismic standard inversion procedures. In addition, the event. This information is valuable because the properties of the very shallow (10's of meters) medium through which the wave propagates layers can be constrained by the determination affects it in a number of ways, and the of the vertical one–dimensional resonance characteristics of the observed motion can be eigenfrequencies. It has been shown that this can used to deduce the properties of the medium be achieved by analyzing the spectral ratio of along the ray path. the horizontal to vertical noise (Nakamura, The basic approach of body-wave 1989). seismology is as follows: given the observation Baseline Mission and Descope Options of the arrival time of a seismic phase (e.g., the As we are proposing only to supply a set of direct P or S arrival) at a number of locations, SP sensors and science participation to the the position (hypocenter) and event time of a larger SEIS experiment, we can identify no quake can be determined. This allows the reasonable descope options short of deleting the determination of the size (i.e., magnitude, or SP portion of the investigation. In this section more precisely, seismic moment) and geologic we will detail the specific contribution of the SP setting of the event, as well as the apparent sensors and the impact to the SEIS investigation velocity of the wavefront. With the if they are deleted. accumulation of data at various epicentral The SP sensors provide two important, distances, travel-time curves (delay vs. distance) distinct elements of the SEIS system. The first can be constructed from which the seismic of these is the third component for the LP velocity as a function of depth can be deduced. seismometer, allowing the reconstruction of the Seismic velocity depends on the density and 3-dimensional ground motion. Without this elastic constants of the medium, and so one can capability it will be difficult to identify shear derive constraints on the composition of the wave arrivals and to analyze surface wave interior at various depths by comparison with phases. Polarization analyses will not be laboratory measurements. In addition to the possible, making the identification of a number direct compressional and shear arrivals, other of important phases problematic and precluding paths can be taken utilizing reflection, anisotropy studies. The inclusion of the second refraction, and mode conversion at mechanical horizontal component will also permit the boundaries (e.g., the crust-mantle boundary) identification of the ray azimuth, which is which can provide additional information about necessary to localize epicenters (especially for their depth. Further information about the tectonic studies) in the absence of multiple- characteristics of the source and the attenuating station detections. properties of the medium can be obtained from The second element is a separate 3-axis the wave amplitude and its spectrum. short-period seismometer. This is necessary in a Shallow Crustal Structure. Although a local UBB system in order to maintain sensitivity array is necessary for detailed local structure across the full spectrum of seismic signals (see determination, a single seismic station can make below). Only with this element will frequencies several types of measurements, which provide above about 5 Hz be usefully detectable. information on the seismic structure in the Absent this information we will lose resolution region of the lander. In particular, these in our ability to determine arrival times, methods may provide information on the

Netlander SEIS: Mars Seismic Network 6 degrading the accuracy of hypocenter locations. microseismometer provided by JPL through Small quakes (located close to the stations) that this proposal. radiate virtually all their energy at high frequencies may go completely undetected. Long Period Sensors (LP). These sensors Information on the rupture process is contained have an extremely high mechanical almost exclusively in the higher frequencies, as amplification due to the low resonant frequency are the diagnostic signatures that allow the of the suspension and can provide a very-low- differentiation of impacts from tectonic events. noise signal in the correct installation. Thus the The wavelengths in this frequency range are of LP sensors are enclosed in an evacuated, order 100 m, ideally suited for investigating the thermally insulating, spherical enclosure. After uppermost layers of the crust using the single- landing, 3 legs that extend through the lander station methods described above. base plate to the underlying surface will raise In addition to these specific science the sphere, disconnecting the seismometers justifications, a further argument for inclusion of from the NetLander structure and coupling the SP sensors is found in the redundancy it them to the Martian surface. Leveling of the provides. The LP sensors are very sensitive instrument sphere is then effected through the instruments with a significant number of stepper motors in the legs. The LP seismometer mechanisms. Although each LP sensor is design has been developed through a CNES designed to a failure-free probability of 95%, Research and Technology Program in there is a corresponding probability of 27% that preparation for the InterMarsnet program. It one of the 8 sensors will fail during the life of uses the heritage of the OPTIMISM the mission. Such a failure will severely seismometer, which was flown on the Russian degrade the quality of the measurement at that Mars 96 Small Stations. For NetLander, only station, due to the nature of the LP’s oblique two oblique mounted sensors can be configuration. accommodated in the sphere due to mass and For these reasons, the inclusion of both the volume requirements of the low-resonant- SP and LP sensors was strongly endorsed by the frequency suspension. One vertical low-noise selection panel for the NetLander payload. VBB output and a single horizontal VBB output (with a higher expected ambient noise) SEIS: Science Implementation will be synthesized from their outputs. The SEIS: Instrumentation second horizontal output will be supplied by an To meet the measurement objectives of high sensitivity across the entire seismic frequency band, two complementary sensor designs have been selected for the SEIS instrument package. At a given frequency, the dynamic range of the expected signal is about 106 (for magnitudes ranging from 1.5, the minimum likely detected, to 5.5, the maximum expected). Moreover, seismic signals are generally flat in displacement, and because the mechanical response of a seismometer is flat in velocity, the 4-decade range of scientifically valuable frequencies results in an additional 104 of required instrument dynamic range. Such a total dynamic range (~ 1010) is impractical to implement in a single instrument, and other high-sensitivity, UBB systems have employed Fig. 6. Seismometer sensitivity as a function a similar dual sensor design (e.g., the Apollo of frequency. Shown are performance ALSEP seismometers). curves for the SP seismometer, the LP The two types of sensors incorporated in seismometer (both as tested and anticipated the SEIS package are a CNES-provided long- from planned development), and the period seismometer and a short period Streckheisen STS-2, a state-of-the-art terrestrial seismometer.

Netlander SEIS: Mars Seismic Network 7 The design of the sensor is based on previous instrument development for a planetary seismometer at JPL. This design uses a micromachined mechanical structure consisting of the suspension mechanism, proof mass and capacitor plates, and a highly sensitive capacitive displacement transducer that Fig. 7. Prototype single-axis employs feedback using electrostatic force microseismometer used in comparison field rebalance. A prototype microseismometer using test with conventional seismometer. a silicon spring is shown in Fig. 7. A comparison of the response from this SP sensor (see below). This VBB instrument prototype and a conventional portable has been designed to study very low seismometer to a small earthquake is shown in accelerations superimposed on a pronounced Fig. 8. The dominant feature in the low- thermal drift. Therefore, the sensor is amplitude terrestrial seismic background, the characterized by high sensitivity (³ 5x104 “microseismic peak”, can be clearly seen with a V•s/m), very low noise (< 10-10 m•s-2 Hz-1/2) period of approximately 7 seconds. and a design relatively insensitive to The suspension incorporates three wafers environmental parameters. bonded and diced to produce a symmetric structure. Details of the design and fabrication Short Period Sensors (SP). Considerably are included in the Mission Implementation smaller and lighter than the LP sensors, these Section. The central wafer incorporates a dual-axis microseismometers will be used both cascaded set of orthogonal flexures (Fig. 9), to augment the LP sensors and to provide allowing motion of the proof mass in two complementary high-frequency seismic data. directions. The flexure geometry is designed to The LP system above incorporates a dual- maximize the robustness of the suspension; axis SP sensor. This sensor will provide a end-stops prevent any motion induced by horizontal axis to allow recovery of the third accelerations greater than 1 g. The proof mass component, albeit with reduced sensitivity at is free to move under gravity in its two low frequencies; see Fig. 6. The other axis of orthogonal directions to an equilibrium this sensor will be vertically aligned, providing position. Capping wafers carry the metallized redundancy for the LP vertical axis. In addition fixed electrodes. to this SP sensor, a pair of dual-axis sensors The displacement signal and feedback will be fixed on a spike in direct contact with actuation result from the changing overlap the ground. These will be orthogonally mounted to sense all three axes of motion, x 10-6 seismic signal vs time again, with a redundant vertical component. 3 Although the spike will not be leveled or have 2 the environmental control of the LP sphere, it 1 0 signal should produce a significantly better high- -1 frequency response due to the direct coupling -2

-3 of the microseismometer to the ground rather 130 135 140 145 150 155 160 165 170 175 than through the spherical enclosure. In x 10-6 addition to a seismic output, tilt information 3 will be provided by their DC outputs. The SP 2 1 sensors are the subject of this proposal, and so 0 signal will be described in more detail. -1 The proposed SP sensors will be produced -2 -3 130 135 140 145 150 155 160 165 170 175 in the Microdevices Laboratory of JPL. They time - seconds are designed to meet the constraints of the mission, in particular having very low mass and Fig. 8. Comparison of seismic traces from a volume, while delivering performance conventional seismometer (top) and the comparable to that of a conventional terrestrial prototype microseismometer. The vertical seismometer over a 0.05 to 100-Hz bandwidth. axis is in units of g.

Netlander SEIS: Mars Seismic Network 8 between electrodes on the fixed plates and the patterned surface of the silicon proof mass. The electrode sets on either face of the proof mass are orthogonal, producing a two-axis output from a single suspension. The use of a lateral detection scheme reduces damping effects and hence the fundamental noise floor by two orders of magnitude compared to the more conventional parallel opposed-plate approach. The small volume of the sensor limits the resonant frequency of the suspension to 10 Hz. This relatively stiff suspension requires a correspondingly sensitive position transducer to measure the deflection of the proof mass. A low-noise switched-capacitance transducer determines the lateral movement between the Fig. 9. Plan view of the center wafer moving proof mass and fixed electrodes above showing the configuration of the proof mass and below the proof mass. and flexures. Motion is in the plane of the Three progressively coarser ranges of wafer. motion are transduced and separately controlled about 200 Mbit/sol. These data will be stored using different feedback schemes. Such an in a 4-Gbit FIFO buffer (partitioned within the approach relaxes the constraints placed on the 8-Gbit total CDMS memory), that has a cycle dynamic ranges of the electrostatic actuator and time of about 20 days. the final digitizer. Details of this scheme are Due to the data volume generated by SEIS, outlined the Mission Implementation section. a “preview and select” procedure will be The seismic signal from each axis is implemented. A low frequency, continuously integrated to produce a velocity output which is sampled, digitally filtered data set will be then anti-alias filtered before being digitized transmitted to the Earth every day, including: with a multiplexed 16-bit analog-digital converter. The overall estimated noise floor of • Low-rate LP data from the vertical and the microseismometer, incorporating thermal horizontal components (tide and general quick noise due to the suspension, transducer noise, look of instrument behavior, only 100Kbit/day) and feedback noise, is shown in Fig. 10. • LP vertical data at 1 sps to identify the fraction of time where full rate data is to be SEIS: Mission Description transmitted The data acquisition process is based on extensive high-rate sampling of all parameters • Spectral amplitudes on the SP vertical and storage in high-capacity on-board memory. output at a rate of 1 multi-spectral estimate/sec. The SP sensors are sampled at the highest rate The NetLander mission plan anticipates of 200 samples per second (sps) for all axes. The LP seismometer’s 2 axes are sampled at a Total (Hz) rate of 100 sps. With housekeeping data, the Ö Thermal total digital stream transmitted to the spacecraft Command and Data Management System Feedback (CDMS) for the seismometer is 1700 bytes/sec. The CDMS will store the data with a time Transducer header with an accuracy of a fraction of a second relative to the Lander. It will digitally filter the data to reduce the final storage rate to

100 sps for the 3-axis SP vertical sensor, 20 spsNoise equivalent acceleration / ng/ for all other seismic outputs (LP and horizontal Frequency / Hz SP) and 5 sps for the housekeeping data. The Fig. 10. Components of the theoretical noise resulting data volume, assuming a compression performance for the SP sensor. a ratio of at least 2 with a lossless delta code, is

Netlander SEIS: Mars Seismic Network 9 daily transmission of these data, amounting to The CONT1 and CONT2 data will be 2.5 Mbits/day. These data will be immediately processed on Earth to identify time periods of analyzed by the seismometer teams in at least interest (e.g., quakes), especially where one of two operations centers to minimize the correlations are found between different turn-around time during regular shift hours stations. Commands will then be sent to the (Paris and Pasadena, UT and UT-8). From this lander to schedule the transmission of the analysis, a set of time periods will be identified corresponding higher frequency EVENT data. and prioritized, and a corresponding table of The raw data will be transformed in a parameters will be uplinked in order to flag and format compatible for rapid exchange and to save that data within the specific CDMS scientific use. The proposed format for seismic buffers of interest (e.g., where quakes are data is SEED format, a seismic exchange tentatively identified). The corresponding full- format integrating all of the key information rate LP and SP data will then be progressively necessary for seismic analysis (time, sampling downlinked as EVENT mode data, at about 5 rate, ID and position of station, pole and zero of Mbits/day. transfer functions, calibration information, After a learning period, an automatic event etc.). Level 0 data, with all packets in order and detection algorithm will be implemented. It missing packets flagged, will be transformed in will be based on a STA/LTA classical event mini-SEED data, with non-validated trigger or on the evolution with time of calibration/time/etc. information. These data compressed power spectral density computed will be used for quick-look analysis and limited on board. More sophisticated programs can be release, for example for press or outreach transmitted from the Earth if necessary. activities. Within one month, preliminary SEED data will be made available for the SEIS: Data Analysis and Archiving consortium members on the SEIS/NetLander The data acquired by the proposed SEIS SP Data center located at the IPGP, Paris for sensor will be an integral part of the complete validation and preliminary science analysis. SEIS data set. As such, it will be subject to Final release of validated data in PDS- NetLander data policies. In this section we approved format (presumably SEED for describe the analysis and archiving plans of the seismic data) will be done within 6 months of SEIS investigation as a whole. data acquisition. A data dictionary conforming Seismic experiments can generate large to PDS standard will be developed, and each amounts of data (>100 Mbits/sol). We will product will be formatted according to the manage this data by using the mass storage on latest PDS usage. Data will be put on-line on board the lander, a low continuous rate sub- WWW servers, including software necessary sampled downlink, and an additional downlink for translation of data from PDS to various of selected full-rate data. The seismic data will common formats used by the terrestrial seismic be collected in 3 different modes. The two first community. Data will also be distributed on modes (CONT1 and CONT2) will be CD-ROMs or the corresponding technology in continuous data streams, with all data 2005, but in all cases supporting formats in transmitted back to Earth. CONT1 is accordance with the recommendations of the continuously sub-sampled data (both seismic FDSN (Federation of Digital Seismic and housekeeping) with relatively low Networks). sampling rates. CONT2 is a continuous spectral analysis, using a moving window, of the LP SEIS: Science Team and SP data. The third mode (EVENT) will As with the other NetLander investigations, make use of the mass memory of the lander. It the science team for the SEIS experiment has will consist of the continuous storage of already been chosen through the competitive seismic data at high sampling rates (100 sps for AO for the NetLander payload, and thus are not the SP sensors, 20 sps for the LP sensors). In the subject of this proposal. The complete team general, all data will consist of time series that is listed in Table 4. Below we include roles will be compressed using delta or Huffmann and responsibilities for only those team lossless algorithms, and collected into 1-kbit members who require NASA funding or have packets for transmission to Earth. The Level 0 direct responsibility for instrument hardware. products are listed in Table 3. Further U.S. participation in the science team

Netlander SEIS: Mars Seismic Network 10 Table 3. Level 0 SEIS Data Products Data Product Sample Rate Description TIDE 1/100 Hz Tidal output from LP sensor (2 chan.) CONT1 LP-C 1 Hz Sub-sampled LP (2 chan.) ENV-C 1/10 Hz Low-rate environment/housekeeping data (4 chan.) SPEC-SP 1 Hz SP spectra CONT2 SPEC-LP 1 Hz LP spectra POS 1/100 Hz LP position sensor output (2 chan.) LP-E 20 Hz LP data (2 chan.) EVENT SP-E 100 Hz SP data (4 chan.) ENV-E 1 Hz High-rate environment/housekeeping data (8 chan.) will be solicited through a Participating W. Thomas Pike (Jet Propulsion Scientist program during the operations and Laboratory) is a Co-Investigator on the SEIS analysis phases of the mission. Science Team. He will be responsible for the W. Bruce Banerdt (JPL) is the Principal design and fabrication of the SP sensors and Investigator for the SEIS SP instrument, and is will take the lead in defining the operational a Co-Principal Investigator of the overall modes and calibration procedures for the NetLander SEIS Science Team. He is instrument. He will perform ongoing SP responsible for the success of the SP calibration during Mars surface operations and experiment and the science investigation will analyze the instrument data to track and associated with it. He will help lead the SEIS maintain instrument performance. science team in defining and developing the science objectives and requirements. He will direct the U.S. science operations effort, and is responsible for the analysis and preliminary interpretation of the SP data. Within the SEIS Science Team he has primary responsibility for determination of near-surface and crustal structure. He is also responsible for representing the interests of the U.S. science community in the NetLander Project and for ensuring that the science community at large has timely access to the complete SEIS data set. Table 4. NetLander SEIS Science Team Domenico Giardini (ETH-Hönggerberg) is Role Institution a Co-Principal Investigator on the overall SEIS P. Lognonné PI IPGP (Fr) Science Team, and is responsible for supplying B. Banerdt Co-PI JPL (USA) the SEIS instrument-level electronics. Within D. Giardini Co-PI ETH (Switz) W. Benz Co-I Univ. Bern (Switz) the SEIS Science Team he has primary D. Breuer Co-I Westfalia Univ. (Ger) responsibility for the analysis of Mars M. Campillo Co-I Grenoble Obs. (Fr) seismicity and tectonics. His effort will be E. Clévédé Co-I IPGP (Fr) funded by PRODEX. P. Defraigne Co-I Royal Obs. Belgium (Bel) Philippe Lognonné (Institut de Physique V. Dehant Co-I Royal Obs. Belgium (Bel) du Globe de Paris) is the Principal Investigator A. Deschamps Co-I UMR (Fr) of the overall NetLander SEIS investigation F. Akio Co-I ISAS (Japan) and will be supplying the long-period sensors J. Gagnepain-Beyneix Co-I IPGP (Fr) for SEIS. He is also responsible for the final J. Hinderer Co-I EOST (Fr) integration of the SEIS instrument package and J.-J. Lévêque Co-I EOST (Fr) for the overall science operations system. Dr. H. Mizutani Co-I ISAS (Japan) A. Mocquet Co-I Univ. Nantes (Fr) Lognonné has primary responsibility for J.-P. Montagner Co-I IPGP (Fr) representing the SEIS experiment to the J. Oberst Co-I DLR (Ger) NetLander Science Steering Group. His effort T. Pike Co-I JPL (USA) will be funded by CNES. L. Rivera Co-I EOST (Fr) T. Spohn Co-I Westfalia Univ. (Ger)

Netlander SEIS: Mars Seismic Network 11 NEIGE: Science Goals and Objectives calibration of the ionospheric effects from the Table 5. NEIGE objectives address fundamental questions of planetary structure and evolution. lander radio signal, enabling the precise Understand the constitution and formation processes of the planets. The objectives of the NEtlander Ionosphere measurements needed for geodesy. The and Geodesy Experiment (NEIGE) are to Space Science Theme Understand the interactions of the atmosphere with the surface and calibrations themselves provide a distributed volatile reservoirs. determine the mineralogy and temperature of measurement of the Martian ionosphere which the deep interior of Mars, provide global Determine the internal structure of Mars in terms of core and mantle is a network science objective in its own right. Investigation Goals radii, mineralogy, and thermal state. sampling of the Martian ionosphere, and The ionospheric science goals are not included provide new information about the interactions Determine the seasonal changes in the polar ice cap mass distribution. here, as they are not part of the US portion of Determine the total and core contributions to the polar moment of of the Martian surface and atmosphere (e.g., the the NEIGE science data analysis. seasonal cycling of CO2). The mineralogy and inertia through measurement of planetary precession and nutation temperature of the deep interior will provide Martian Interior; Precession and Nutation Science Objectives · Infer the size, and physical state of the core. key information on the accretion of the planet, Little is currently known about the interior Determine the seasonal changes in length of day and polar motion and, more generally, can be used to test of Mars. The only in situ observations are · Estimate the seasonal changes in CO2 ice distribution. theories of terrestrial planet accretion and those of the Martian gravity field and polar thermal evolution. These objectives (Table 5) moment of inertia, which are derived from Table 6: NEIGE Instruments and Subsystems: shaded items are needed to support all instrument are high priority items in NASA’s Roadmap for radio tracking of orbiting and landed spacecraft telemetry; other items are NEIGE-specific. Solar System Exploration, and are highlighted (e.g. Smith et al., 1998; Folkner et al., 1997). Instrument/Sub-System Supplier Heritage in the notional Mars Network mission. These observations are the main constraints for Lander UHF antenna CNES Mars Balloon Relay (MBR) interior models principally based on Geodesy involves measurement of the Lander UHF receiver CNES Mars Balloon Relay (MBR) changes in locations of the crust with respect to extrapolation of the Earth’s internal structure to the lower pressures of Mars' interior (see Fig. Lander UHF transmitter CNES Mars Balloon Relay (MBR) inertial space due to planetary rotation. Lander telemetry coder/decoder CNES ROSETTA Geodesy is a major method of studying the 12) and analysis of SNC meteorites. Geochemical studies argue in favor of relative Lander carrier lock transponder CNES ROSETTA interior of planets, complementing information Lander X-band transmitter CNES X-Ray MultiMirror (XMM) mission provided by seismology. enrichment in iron of the Martian mantle (mainly composed, as for the Earth, of olivine) Lander X-band antenna CNES X-Ray MultiMirror (XMM) mission NEIGE will provide improved estimates of Orbiter UHF antenna CNES Mars Balloon Relay (MBR) Mars' precession and nutation, polar motion, with respect to the Earth’s mantle, and relative enrichment in sulfur content of the iron core. Orbiter UHF transmitter CNES Mars Balloon Relay (MBR) and length-of-day variations. The primary Orbiter UHF receiver CNES Mars Balloon Relay (MBR) observations will come from monitoring the The theoretical calculations of planetary Doppler shift on the radio signal between the thermal evolution that incorporate this Orbiter telemetry coder/decoder CNES ROSETTA NetLanders and the supporting hypothesis lead to values of the outer core Orbiter Doppler counter JPL GRACE communications orbiter (Table 6, Fig. 11). radius ranging from 1550 km to 1850 km, i.e., Orbiter X-band receiver JPL Mars PATHFINDER Additional measurements of the radio signal 45% to 55% of the mean surface radius of the Orbiter X-band antenna JPL Mars PATHFINDER from the landers may be made at Earth, if two planet (e.g., Schubert and Spohn, 1990; NetLanders are simultaneously in view of the Schubert et al., 1992; Zharkov et al., 1991; communication orbiter. Sotin et al., 1996; Sohl and Spohn, 1997). The The improved precession estimate will give measured polar moment of inertia implies a a much more accurate estimate of the polar core radius between 1300 km and 1700 km, moment of inertia, which is a strong constraint which is compatible with the theoretical on the interior mass distribution. The estimates. The question of whether the core is measurement of nutation will determine liquid or solid is still an open question. whether the Martian core is still fluid and The size, mineralogy and thermal state of provide constraints on its size. The polar the core are crucial for understanding the motion will provide detailed information on the accretion and internal structure of planets. By mantle elasticity. assuming that the Martian core has a nearly NEIGE will also improve the determination adiabatic temperature gradient, it is possible to of the obliquity rate, and therefore the past model the core with very few parameters. If the climate of Mars. Such a constraint will be core is liquid, such parameters will be the necessary for understanding the structure of the density, the adiabatic bulk modulus, the core- polar layered terrain and the polar ice caps. mantle boundary radius and temperature (the The Doppler shifts of the radio signal from shear modulus being by definition zero for a the NetLanders to the communications orbiter liquid core). Other parameters, such as partial will be measured at two different radio derivatives of density and adiabatic modulus Fig. 11: Block diagram of the radio system for the NetLanders and the primary supporting frequencies which are affected differently by with temperature and pressure, can be derived orbiter. The components contributed by the U.S are shown in blue; additional items needed for the Martian ionosphere. This will allow from high-pressure laboratory experiments, NEIGE and contributed by CNES are shown in red.

NetLander NEIGE: Mars Geodesy Network 12 The nutation driven by the Sun has a total amplitude of about 1000 mas (milliarcseconds), corresponding to a displacement of 16 m at Mars' surface. The Mars' FCN resonance contribution, depending on the FCN period (expected to be about 230 to 280 days, for a planet in hydrostatic equilibrium) could be of the order of several tens of mas, or to several tens of cm at the surface. The observation of the amplitude of the nutations close to the FCN period will then allow to determine if the FCN exists (if the core is liquid or solid) and to determine the parameters involved, in particular the core-mantle boundary flattening. For Mars, nothing is known about the Fig. 12: Comparison between the interior existence of an inner core. From the recent of Earth and Mars. missions to Mars, it is found that there is at for each type of admissible mineralogy of the present no (or almost no) contribution to the core, probably with smaller errors. Therefore, external magnetic field from an internal field. the determination of mineralogy and Consequently, the core should be either temperature of the core will be practically completely liquid or completely solid (e.g., equivalent to the determination of the four Longhi et al., 1992). An almost completely independent parameters described above. These liquid core (very small inner core), or an almost can be determined by means of geodetic and completely solid core (very large inner core) seismic observations. would probably also be possible. Van Hoolst et Even if the core radius is known (e.g., al. (1999b) have examined the effect on the through seismology), the current uncertainty in FCN of an inner core varying in size. The the moment of inertia, ±0.5 %, leads to a ±3.3% consequences on the FCN period and error in the density of the core. This results in a consequently on the resonance in the nutation ±33% error on the temperature, i.e. larger than transfer function are important when the inner the differences in temperature of the already core is large. published temperature models of Mars. We Atmosphere/Surface Interactions; Length-of- expect an improvement by a factor of about 5 Day and Polar Motion of the moment of inertia by NEIGE through Variations in Mars' length-of-day (LOD) improved determination of Mars' precession. are caused by sublimation/condensation of the This will reduce the error to a level useful for ice caps, winds, and solar tides. The ice cap and real constraints on the core temperature atmospheric effects are the most important, (determined at 5%) and on the mineralogy with expected annual (semi-annual) variation (core density error level of 0.6%). corresponding to an amplitude of 6 m (5 m) at The size and state of the core can also be the equator. The winds contribute about one determined by accurate measurements of Mars' third of the total effect. The contribution due to nutation. In particular, when the core is liquid, solar tides is about 30 cm (15 cm) for the the nutations driven by the gravitational force annual (semi-annual) effect. By observing the of the Sun with frequencies at multiples of the amplitude of the length-of-day variations of orbital frequency are influenced by a resonance Mars, correcting them for the tidal effects, we effect due to the free core nutation (FCN). The will estimate the changes in the ice cap masses. FCN is a normal mode that only exists if the The effects on Mars rotation, due to the core is liquid (see Van Hoolst et al., 1999a, winds and to the mass variations associated 1999b, Dehant et al., 1999a, 1999b, 1999c). It with the sublimation/condensation process in is related to the fact that one can excite an the ice cap and in the atmosphere, have been angle between the rotation axis of the core and estimated, as for the polar motion, from a LMD the rotation axis of the mantle. dynamic meteorological model (Defraigne et al., 1999b). Comparing these predicted

NetLander NEIGE: Mars Geodesy Network 13 amplitudes with the expected precision of the describes the induced mass redistribution due NEIGE experiment of NetLander, it appears to external forcing. The observation of the that the induced LOD variations will be well Chandler Wobble period will thus lead to above the measurement precision: the annual information about elastic and inelastic component will be at the level of 0.2 ms (this parameters of the mantle. corresponds to an effect on UT of 25 ms, i.e., 6 m on the equator) and a semi-annual Baseline Mission and Descope Options contribution at the level of 0.4 ms (this The baseline NEIGE mission is to carry out corresponds to an effect on UT of 22 ms, i.e., 5 weekly measurement campaigns of radio m on the equator). The precision of NEIGE is Doppler shifts, between the orbiter and each expected to be better than 0.004 ms for the NetLander and between the orbiter and Earth. LOD variations, corresponding to 12 cm on the For the NEIGE campaigns, Doppler equator for the annual and 6 cm for the semi- measurements from each NetLander would be annual contribution. made during a 24-hour period. Two-way Another effect that must be taken into Doppler measurements between the orbiter and account when analyzing observations of LOD Earth would also be taken during the same variations is the tidally induced component. 24 hour period, for about 8 hours. The lander The LOD transfer function of Mars can be radio system will be funded by CNES. The computed by numerical integration of the Doppler counter (and X-band radio receiver) equations of motion, from the center of the are proposed to be funded by NASA under this planet up to the surface. The transfer functions proposal. so-obtained for different models of Mars' The NEIGE baseline is based on weekly interior can be multiplied by the amplitudes of measurements over one Martian year. Because the zonal tide-generating potential of Mars the signatures of interest have annual or given by Roosbeek (1999). The amplitudes seasonal variation, there is no need for more obtained for the annual and semi-annual frequent measurements. It is also not essential components are both of the order of 0.01 ms that measurement be made each week; a few (this corresponds to an effect on UT of 1 ms for missed or failed campaigns do not significantly the annual component and 0.5 ms for the semi- affect the results. However, at least one-half annual component, i.e., 30 cm on the equator Martian year needs to be sampled to be able to for the annual and 15 cm for the semi-annual separate annual from seasonal effects. contribution). These are just above the A possible descope could be achieved if precision of NEIGE and must be considered. two or more NetLanders could be The polar motion of Mars (i.e., the motion simultaneously viewed by a (high-altitude) of the axis of rotation in a reference frame tied Martian orbiter capable of transmitting to more to Mars) is expected to have an amplitude of than one NetLander at a time. It might then be 0.5-1 m. It is dominated by two components: possible to receive the NetLander X-band radio signal on Earth, with the frequency effects of • a seasonal component, with an the orbiter radio signal canceling between the amplitude of about 30 cm, related to the two NetLander signals. Then it might not be winds and the surface mass redistribution necessary to have the Doppler counter on the caused by atmosphere and ice cap orbiter, a large potential savings. However, this sublimation/condensation process, and scenario has not yet been thoroughly analyzed • a component related to a free oscillation and might yield a greatly reduced science of the planet similar to the Chandler result, so must be considered a high-risk de- Wobble in the Earth’s polar motion. scope. It would be possible to investigate this The amplitude of the Chandler Wobble option during the initial stages of the mission component has been estimated to be about 10- development. 80 cm (partly based on observed variations in the surface pressure) (Yoder and Standish, NEIGE: Science Implementation 1997). Its period is about 200 days, and is directly related to the global Mars dynamical NEIGE: Instrumentation flattening and the Love number k, which NEIGE is based on measurement of the orientation of the surface of Mars with respect

NetLander NEIGE: Mars Geodesy Network 14 Fig. 13. a) Primary observation geometry. b) Secondary observation geometry. to inertial space. The orientation of the surface NEIGE: Mission Description is determined by measuring the Doppler shifts Observation Plan of radio signals between the landers on Mars and an orbiter. The position of the orbiter in NEIGE measurements involve variation of inertial space is determined by tracking the Martian rotation over periods from several Doppler shift of the orbiter’s radio signal with months to a Martian year, with dual-frequency tracking stations on Earth. The NetLander Doppler measurements obtained once per radio signal may also be measured directly by week. Each week, an 8-12 hour period will be Earth tracking stations. The orientation of the identified during which the communications Earth tracking network is known with respect orbiter will be able to observe at least three of to inertial space by Very-Long Baseline the NetLanders. During this period, each Interferometry measurements of quasars, NetLander will send coherent radio signals to supplemented by observations of Earth-orbiting the orbiter at UHF and at a second carrier spacecraft. frequency. Also during this period, a special The instrumentation needed for NEIGE tracking pass of a DSN 34-m station will be consists of special radio components on both dedicated to tracking the orbiter and possibly the NetLanders and on a Martian orbiter. The also the second NetLander carrier signal. block diagram of the overall radio system (Fig. Under the primary plan, the orbiter would make 11) shows which components are needed for accurate measurements of the NetLander support of all NetLander investigations and Doppler shifts and relay them to Earth. When which are needed specifically for NEIGE. For in view of the DSN tracking station, the orbiter NEIGE, the NetLander radio system must be would also transmit an X-band signal coherent capable of receiving a carrier signal from an with a signal received from the DSN station. orbiter and transmitting radio signals at two The Earth and orbiter tracking data would be widely separated frequencies, each coherent acquired, verified, and calibrated by the NEIGE with the signal received from the orbiter. The science team. The combined Earth and orbiter orbiter radio system must be capable of tracking over the NetLander operational period generating a continuous radio signal for would be combined to solve for the Martian reception by the NetLanders and receiving the geodesy parameters. The geodesy parameters two return signals from the landers. In will then be used to constrain models of the addition, for the primary NEIGE observation interior. mode, the orbiter should also very accurately Observation geometry measure the Doppler shift of the NetLander The primary NEIGE measurements are signals, at both frequencies, relative to the accurate measurements of the Doppler shift of transmitted signal. the NetLander radio signals received by the The lander radio system, including the dual- communication orbiter, and accurate position frequency coherent transponder, is to be funded knowledge of the orbiter’s position with respect by CNES. Funding for the dual-frequency to the Earth. The primary observation Doppler measurement instrument to meet the geometry is indicated in Fig. 13a. Use of an NEIGE requirements is being proposed here for orbiter as an intermediate position reference inclusion on the communications orbiter. (between the orientation of the Martian surface with respect to inertial space, as determined by measurement at Earth) places stringent

NetLander NEIGE: Mars Geodesy Network 15 requirements on the lander and orbiter’s radio the planning orbits for Mars Express. Doppler measurement systems and on tracking of the measurements were also simulated between the orbiter by the Earth. One of these requirements orbiter and an Earth tracking station. The is that the NetLanders transmit a radio signal at positions assumed for the three landers are an additional radio frequency, which must be given in Table 7. different from the UHF data carrier frequency, Measurements were simulated for one 8- to calibrate the effect of Mars’ ionosphere on hour pass each week. Each tracking pass observed Doppler shifts. included Doppler measurements between the This additional carrier frequency enables a orbiter and the Earth tracking station covering secondary observation geometry where the an 8 hour period (when the satellite was not additional NetLander radio frequency is occulted by Mars). The Doppler data accuracy observed at the Earth. The NetLander radio is was assumed to be 0.1 mm/s for measurements designed to transmit both data and the taken at 60 second intervals, typical for DSN additional radio carrier, through omni- radio tracking experiments. Doppler directional antennas. measurements between each NetLander and the The NetLander radio system transmits orbiter were also simulated. The two-way enough power so that the radio carrier signal Doppler accuracy for the lander-orbiter link (but not data) can be received at a large radio was assumed to be 0.1 mm/s, the same as the antenna on Earth. The reception of the orbiter-Earth link. NetLander radio signal on Earth would largely The use of the orbiter as an intermediate eliminate the need to very accurately determine reference makes the estimation of the the position of the Martian orbiter required for orientation of the Martian surface highly the primary NEIGE observation geometry. The dependent on the accuracy with which the secondary NEIGE geometry requires that a orbiter’s position is determined. Currently the Martian orbiter transmit to two NetLanders position uncertainty of Martian orbiters, based simultaneously while the NetLander signals are on DSN tracking, is of order 1-10 m. This is received at Earth. This simultaneous limited primarily by the uncertainty in the transmission is needed to remove the noise due Martian gravity field and its effect on the to the orbiter frequency reference. orbiter’s trajectory. However, the additional Simultaneous reception of signals from two measurements between the orbiter and the NetLanders greatly reduces the noise on the NetLanders will allow for much improvement radio signal measurements (e.g. solar wind, in orbit determination. The expected accuracy Earth ionosphere and troposphere) that were is comparable to that of Earth-orbiting satellites the limiting errors on the Mars Pathfinder which receive signals from the fixed DORIS mission and leads to improved geodesy radio transmitters. With DORIS tracking, the measurements. This secondary observation orbiter position uncertainty can be reduced to a geometry also has fewer requirements on the few cm. orbiter radio signal than the primary Table 8 gives the results for the expected observation geometry, but is more dependent uncertainties of the Martian rotation constants on the shape of the orbit and timing of from the simulation cases. The a priori measurements (simultaneous visibility of the uncertainties are based on present knowledge orbiter and the Earth at two NetLander sites). from the Viking and Pathfinder missions. In Table 8, Case 1 indicates the accuracy that NEIGE simulations could be achieved if the Martian gravity field Detailed computer simulation of the NEIGE was perfectly calibrated, while Case 2 indicates experiment shows that great improvements can the accuracy that would be achieved if the be achieved in the knowledge of Mars’ rotation Martian gravity field uncertainty remains the over that obtained from the Viking and same as it was prior to the Mars Global Pathfinder landers. Surveyor mission. The actual gravity field by Doppler measurements were simulated between each of three landers and an orbiter. Table 7: Landing sites for geodesy study. The orbit assumed was taken to have period 5.7 Lander site 1 site 2 site 3 hours, periapsis 300 km, apoapsis 8300 km, longitude 84.9 E 94.8 E 118.3 E and inclination 122 degrees, which was one of latitude 16.0 -12.1 35.1

NetLander NEIGE: Mars Geodesy Network 16 a priori Case 1 Case 2 Length-of-day annual variation (ms) 100 0.2 0.5 Length-of-day semi-annual variation (ms) 100 0.05 1 Polar motion annual variation (mas) 100 2 4 Polar motion semi-annual variation (mas) 100 2 4 Moment of inertia (%) 0.5 0.1 0.2 Core moment of inertia (% of global Mars' value) 100 17 34 Table 8: Estimated uncertainties in Martian rotation parameters from simulations of the NEIGE experiment. Cases 1 and 2 assume two-way Doppler links from each lander to the orbiter for one hour per week and one 8-hour two-way Doppler link between the Earth and the orbiter per week. Case 1 assumes perfect modeling of the orbiter dynamics; Case 2 includes estimation of adjustment of the Martian gravitational field for each orbit. the time of the NetLander analysis is likely to orbits. An updated model is needed for the be closer to Case 1 than to Case 2. The results rotation of Mars to allow for the estimation of of this simulation display the significant correct geophysical parameters (precession and improvements that NEIGE would make in our rotation variation). The data will be processed understanding of the rotational dynamics of continually as acquired, with final estimates of Mars. geophysical and other parameters one year after the end of the lander mission. NEIGE: Data Analysis and Archiving The data will be archived after the end of The NEIGE level-0 data (Table 9) consist the mission with the Planetary Data System in of the Doppler shifts of the NetLander signals accordance with the NetLander data policy. as received at the orbiter (at UHF and X-band) and the range and Doppler shift of the orbiter NEIGE: Science Team signal as measured at the DSN (at X-band). The Dr. William M. Folkner (JPL), Co- DSN will also supply calibrations for Earth Principal Investigator for NEIGE, will have troposphere and ionosphere. The lander-orbiter primary responsibility for the US portion of data will be received as telemetry from the NEIGE. This includes oversight of the orbiter orbiter. The data will be validated by radio Doppler system for delivery and comparing the observed range values with integration into the telecommunications orbiter, nominal values calculated by nominal Mars development of data analysis software, rotation and orbital models. The validated data coordination with the DSN for receipt of will be converted to a simple text file for Doppler and telemetry data, and data analysis distribution and archiving. The text file will and data archival. He will be funded by NASA consist of one line for each measurement, and through this proposed investigation. will include received UTC at the station, Dr. Robert A. Preston (JPL) will be observed two-way range or range-rate, station responsible for negotiation of interfaces identifier, and ionosphere, troposphere, and between the Doppler radio system and the thermal calibrations. The validated data will be orbiter project team, for international delivered two weeks after receipt of all data agreements involving the NetLanders and from the mission and the DSN for that pass. associated data interface agreements, for The calibrated data will be fit with a experiment planning, and for aiding with the modified version of the software already data analysis. He will be funded by NASA developed to analyze the Viking lander ranging through this proposed investigation. data for estimation of the Earth and Mars Table 9. Level 0 NEIGE Data Products Data Product Sample Rate Description LANDER- DOPL-UHF 1/10 Hz Lander Doppler shift at orbiter at UHF PASS DOPL-X 1/10 Hz Lander Doppler shift at orbiter at X-band ORBITER- DOPO-X 1/60 Hz Orbiter Doppler at DSN at X-band PASS RANO-X 1/600 Hz Orbiter range at DSN at X-band

NetLander NEIGE: Mars Geodesy Network 17 Dr. Charles F. Yoder (JPL) will be responsible for development of Mars rotation models and for interpretation of geophysical parameters. He will be funded by NASA through this proposed investigation. Dr. Jean-Pierre Barriot (CNES), Principal Investigator of NEIGE, has overall responsibility for the experiment and will be primary point of contact for NEIGE to the NetLander project office. He, together with the CNES technical team developing the lander radio system, will ensure that the performance of the radio-system hardware is compatible with the scientific objectives. He will coordinate the data analysis efforts of the separate geodetic data analysis teams (US, French, and Belgian) to allow each team to validate its software. He will oversee development of the data analysis software and lead the data analysis. He will be funded by CNES for NetLander related activities. Dr. Véronique Dehant (Royal Observatory of Belgium), Co-PI for NEIGE, will be responsible for software development and data analysis for the Belgian contribution to NEIGE. She will lead a group to develop models for the interior of Mars and interpret the estimated geodetic parameters in terms of interior models. She will be funded by ESA through a Belgian government office (SSTC) for her NetLander- related activities.

NetLander NEIGE: Mars Geodesy Network 18 Table 10. ATMIS Objectives address fundamental questions of planetary climate and evolution. ATMIS: Science Goals and Objectives thermal tides, stationary Rossby waves, transient Theme Understand the current weather and climate on Mars The NetLander ATmospheric and baroclinic waves, and the large-scale flow that Acquire coordinated meteorological measurements from a network of 4 sites to characterize results as ~25% of the atmosphere condenses and Investigation Meteorological Instrumentation System Goals the processes that drive the thermal structure and dynamics of the Martian atmosphere, and (ATMIS) will make coordinated atmospheric sublimates from the polar caps over the annual the atmosphere’s response to these processes. measurements from a network of 4 stations. cycle (Zurek et al., 1992). These models also Surface/Atmosphere Interactions through the Boundary Layer: ATMIS will record the atmospheric density confirm that the solar forcing of the Martian · Quantify heat, mass, and momentum fluxes vs. time of day, season, and latitude. structure as the probes descend through the weather and climate is modulated by variations · Discriminate effects of surface albedo, thermal inertia, slopes, and roughness. Martian atmosphere, and then make time- in surface albedo, thermal inertia, topographic · Identify processes that lift and transport dust (dust devils, dust storms). slopes, and airborne dust (Segal et al., 1997). · Estimate current rate of aeolian weathering of the surface. resolved measurements of the atmospheric Science · Monitor surface/atmosphere exchanges of water over diurnal/seasonal cycles. pressure, soil and atmospheric temperature, Unfortunately, neither small-scale dust devils nor intense large-scale dust storms can be Objectives General Circulation and Climate wind velocity, humidity, and dust optical depth · Identify the main components of general circulation, including the Hadley circulation, for at least one Martian year (Table 10). predicted by existing models, which rarely thermal tides, stationary Rossby waves, transient baroclinic waves, and the net mass flow indicate wind speeds strong enough to raise dust. ATMIS is an international experiment led associated with the CO2 cycle. by the Finnish Meteorological Institute (FMI), The processes that control the exchange of water · Determine interannual climate variability from Viking to NetLander epochs. with hardware from Britain (Oxford U.), vapor and ice between the surface and · Understand the vertical structure of the atmosphere. France (Service d’Aéronomie), Denmark atmosphere are also poorly constrained by (Risoe Institute), and the US (JPL). These existing models and measurements. An Table 11: ATMIS Instruments and Subsystems (JPL contributions highlighted): contributions are summarized in Table 11 and improved understanding of these and other Instrument Sensor Technology Supplier Heritage Fig. 14. Here, we request NASA funds to phenomena in the Martian atmosphere is Atm. Structure 3-axis accelerometer, 3 axis gyro FMI, Finland MPF, MPL support the JPL-supplied atmospheric essential for Mars exploration because this will Pressure Capacitive aneroid barometer FMI, Finland Huygens , Mars 96, MPL temperature and wind instruments, and US be the working environment for future robotic Humidity Capacitive hygrometer FMI, Finland Mars 96, Earth Radiosonde participation in the analysis of the atmospheric and manned missions. Surface Temperature PRT and thermocouples Risoe Inst., DEN Viking, MPL structure and surface meteorology data. Measurements Needed: Because the Atm. Temperature Thin-wire thermocouples JPL Viking, MPF, MPL Background: The thin, predominately CO processes that drive the Martian weather and Wind Speed/Direction Directional hot-wire anemometer JPL MPL 2 climate vary over a broad range of spatial and atmosphere of Mars varies on a wide range of Dust/Ice Optical Depth Imager with dust, ice, O3 filters Service d’Aéronomie, FR Mars 96 spatial and temporal scales. Remote sensing temporal scales, simultaneous measurements ATMIS/ELF Boom Hinged, 2-segment, carbon-fiber Oxford U., UK ESA Smart-1 Mag Boom

observations from Earth-based telescopes and from a network of surface stations are needed to (a)

Mars orbiters show that the climate exhibits understand and predict their relative effects. MPF Pressures

Long-lived stations are needed because these P(mbar) large variations in temperatures, airborne dust, Dust

and water vapor (Zurek et al., 1992). They also processes vary over the seasonal cycle. devil

To address these issues, the NetLander (c)

revealed the growth and decay of the seasonal Time (hours) polar caps, dust devils, and intense episodic ATMIS instruments will record 4 new (d) regional and global dust storms (Fig. 15). In- atmospheric temperature profiles during entry, situ meteorological measurements acquired by and then make simultaneous, time-resolved the Viking and Mars Pathfinder (MPF) Landers meteorological measurements at the surface for

have confirmed these results, and revealed a at least one Martian year. ATMIS pressure, (b) variety of phenomena with temporal and spatial temperature, wind, humidity, and dust data can scales that cannot be resolved from orbit. These be combined with electric field measurements by include near-surface temperature fluctuations the NetLander ARES experiment to establish the as large as 10 K in 10 seconds, gusty winds relationship between these parameters at the associated with local free and forced Martian surface for the first time. Finally, convection, large-scale slopes, passing weather simultaneous measurements from the 4 landing Fig. 15: (a) MGS Mars Orbiter fronts, (Zurek et al., 1992), super-adiabatic sites will be incorporated into Mars General Camera images of dust devils and vertical temperature gradients (>15 K/meter), Circulation Model (MGCM) to discriminate the dust streaks (MSSS, 2000). (b) Dust and passing dust devils (Schofield et al., 1997). effects of topographic slopes, surface albedo and storm near the south polar cap They also recorded atmospheric pressure thermal inertia contrasts, and atmospheric imaged by Viking Orbiter 2. (c) variations on time scales ranging from seconds dustiness on the general circulation. These Dust devil pressure signature (dust devils, Fig. 15c), to hours (diurnal MGCM experiments will also provide an recorded by MPF. (d) Mars GCM thermal tides), to weeks (fronts), to seasons (the improved understanding of the low-latitude wind predictions. 25% annual pressure cycle). Hadley circulation and other large-scale features Models show that these phenomena are of the Martian weather and climate (c.f. Haberle embedded in a general circulation characterized et al., 1999). Fig. 14: Color-coded block diagram showing distribution of ATMIS sensors and electronics. JPL contributions are by low-latitude Hadley cells, atmospheric shown in gold.

NetLander ATMIS: Mars Meteorological Network 19 Temperature and Wind Measurements: deceleration measurements taken during the This proposal requests NASA funding for the MGS aerobraking phase (Bougher et al., 1999). ATMIS temperature and wind sensors. The 4 NetLander profiles will more than Temperatures must be measured at several double the number of atmospheric profiles for heights within 1-2m of the surface to resolve Mars. The near-simultaneous acquisition along the large vertical temperature gradients, which 4 atmospheric trajectories will enable the first change from super-adiabatic during the day to study of horizontal variability in atmospheric strongly stable at night (Fig. 16; (Schofield et structure over a wide altitude range. Each al., 1997). Viking and MPF measurements NetLander includes a 3-axis accelerometer with show that surface winds are typically weak (1 - capabilities similar to those of the Mars 10 m/s) and gusty, and change direction Pathfinder ASI science accelerometers (1-mg regularly throughout the day in response to the sensitivity between 0 and 31 g). They will be forcing by regional slopes. However, the located near the entry vehicle’s center-of-mass Viking Landers detected much larger winds (CM) to minimize spurious signals generated during the passage of fronts and during dust by the angular accelerations of the vehicle storms. MPF also observed small-scale dust about its CM. They will be sampled at 32 Hz devils that had wind speeds as high as 60 m/s between ~150 km altitude and the surface, (Seiff, et al., 1999). yielding ~768 kbits of data with vertical and Accurate, time-resolved measurements of horizontal resolutions of better than 60 m and the near-surface temperatures and winds are 250 m, respectively. essential for our understanding of the processes that control the exchange of heat, momentum, Value to NASA Solar System Exploration: and water between the surface and atmosphere. An improved understanding of the thermal For temperatures, absolute accuracies of +2 K structure and dynamics of the middle and upper and relative accuracies better than +0.1 K are atmosphere of Mars is essential for making needed between ~170 and 300 K. For winds, reliable predictions for the aerobraking and accuracies of ~10% in wind speed and direction are needed over the range of 0.1 to 80 m/s. The proposed system meets these requirements. Atmospheric Structure Measurements:

Additional measurements of the atmospheric vertical structure are needed for studies of Top TC

processes that transport heat and momentum Bottom TC vertically in the Martian atmosphere. They are also needed to enable reliable predictions of conditions for aerobraking and aerocapture of future spacecraft. Atmospheric densities

should be measured over a wide altitude range

at numerous locations, local solar times, and Top TC

seasons. These observations should have high Mid TC vertical and horizontal resolution (<1 km) to Bottom TC characterize both the mean structure and eddies (including thermal tides and gravity waves). The only continuous high spatial resolution profiles of atmospheric density, pressure, and temperature between the thermosphere and the surface (~140 km to surface) were made during the entries of Viking (Seiff and Kirk, 1977) and MPF (Schofield et al., 1997; Magalhães et al., Fig. 16: (a) Diurnal temperature variations 1999), as shown in Fig. 17. Additional in situ recorded by MPF ASI/MET. measurements of the upper atmosphere (110- (b) Temperature differences measured by 140 km altitude) have been derived from the top, middle and bottom sensors on the mast (2-minute averages).

NetLander ATMIS: Mars Meteorological Network 20 aerocapture of future Mars spacecraft. Improved constraints on the properties of the Martian planetary boundary layer are also needed because this will be the working environment for future landers, rovers, and manned missions to Mars. The NetLanders will provide this information at 4 new sites. Participation by U.S. scientists in this mission will facilitate the quick infusion of data from the NetLander mission, which should facilitate future mission planning. Baseline Mission and Descope Options The Baseline ATMIS experiment includes all of the science and measurement objectives described above. The proposed wind and temperature sensors are highly integrated and will be batch fabricated and calibrated. This approach is cost effective, but offers few effective descope options. It would however be possible to deliver working atmospheric Fig. 17: MPF atmospheric structure profile temperature system if the wind sensors could showing CO2 condensation curve and not be produced. This descope could provide evidence for thermal tides, small scale up to 6 months of schedule margin, but it is gravity waves and a water ice cloud near the unlikely to produce significant hardware cost tropopause (10km). savings because the bulk of the wind sensor cost must be committed at project start, to will be used for the Atmospheric Structure purchase long-lead-time components in the Investigation (ASI). Table 11 lists these wind sensor control electronics. About 1/3 of instruments, along with their sensor type, the proposed ATMIS contributions are for supplier, and flight heritage. The ATMIS block science team participation. If the wind sensors diagram (Fig. 14) shows their layout. are descoped early in the implementation The wind and temperature sensors will be phase, up to $1M could be saved by reducing installed on the 1-m ATMIS/ELF boom the level of science participation in the (supplied by Oxford University). The mass calibration, algorithm production, and allocated for these sensors is 30 grams. Their operations of these instruments. Because the electronics will be installed in the on a 5x7x1- NetLanders will fly with or without the cm daughter board that is mounted on the main instruments proposed here, the performance ATMIS board in the warm electronics box. The floor includes no US instruments or mass of this daughter board and cables is <120 participation in the ATMIS science team. grams. The peak power allocated for these JPL-supplied components is 365 milliWatts. ATMIS: Science Implementation ATMIS: Instrumentation JPL was selected to provide atmospheric temperature and wind sensors for ATMIS, Atmospheric Temperature Sensors: For based on designs developed and flight qualified each of the 4 NetLanders, we will provide 3 for Mars Polar Lander (MPL) MVACS. This atmospheric temperature sensors, which will be proposal requests funding to support the mounted at ~25, 50, and 90 cm above the deck implementation and operations of these on the ATMIS/ELF boom. Like Viking, MPF, instruments, and our participation in the and MPL, ATMIS will use thin-wire (75-mm ATMIS Science team. The other ATMIS diameter) chromel-constantan (type E) instruments include atmospheric pressure, thermocouples (TC’s) to measure the humidity, dust optical depth, and soil atmospheric temperature. Each of the 3 Y- temperature. In addition, the Entry, Descent, shaped TC Brackets holds 3 TC’s, which are and Landing System (EDLS) accelerometers connected in parallel for redundancy.

NetLander ATMIS: Mars Meteorological Network 21 Because TC’s measure only the temperature difference between their sense and reference Fig. 18: MPL/ MVACS Wind junctions, the reference junction temperature wind and temperature Sensor must be known to yield absolute temperatures. sensors provide the To do this, the reference junctions for all 3 heritage for ATMIS. ATMIS TC’s will be located on an isothermal Thermocouples (TC’s) block (IB), whose temperature is recorded by a are used to measure precision platinum resistance thermometer atmospheric TC (PRT). This approach was used in all earlier temperature and wind Mars Landers. For ATMIS, the IB and its PRT direction, and a hot wire are incorporated into the base of the wind anemometer is used for sensor, at the top of the ATMIS/ELF boom. The signals from the TC’s and their reference wind speed. PRT will be transmitted from the IB to the electronics box on shielded copper cables, mm) layer of conformal coating polymer where they will be amplified, digitized, and (Parylene) to produce a strong composite stored. structure. The hot wires are supported on tapered posts that are inserted through the Temperature Data Rates: To resolve rapid centers of a pair of 25-mm diameter, 1mm thick temperature variations, TC’s must be sampled fiberglass disks that form the top and bottom of at 0.2 to 1 Hz. A single temperature sample the wind sensor (Fig. 18). The two fiberglass includes the 3 TC assemblies on the mast, the disks are separated by a truss consisting of six voltage and current of the IB PRT and one 0.5mm diameter stainless steel wires. This reference (zero point) TC mounted on IB PRT disk/truss structure provides the support needed (Table 12). Each measurement is recorded as a and introduces little dynamical obstruction or 16-bit word. If the sampling rate is 1 Hz, the thermal contamination. data rate is 96 bits per second (bps). If samples The direction of the heated plume that is are collected for 5 minutes every 30 minutes blown downwind from the hot wires is detected (25 times/Sol), the total data volume is 720 by one of the 20 TC arrays that surround the kbits/Sol. These data will be calibrated on hot wires (Fig. 19). These TC’s are spaced at board and averaged over each 5-minute interval 18o angular increments, yielding a wind or transmitted directly to Earth. direction resolution of +9o. Each direction TC The NetLander Wind Sensor: array includes 2 thin-wire (75-mm) chromel- The horizontal wind velocity at the top of constantan TC’s that are wired in parallel for the ATMIS/ELF boom will be monitored by a redundancy. These TC’s are identical to those directional, constant-over-temperature, hot- used to measure temperatures, but they are wire anemometer, like that developed by our connected differently, such that they measure team for MPL MVACS (Fig. 18). The the temperature difference from one side of the MVACS-derived control circuit maintains the hot wire to the other, instead of the ambient hot wire at 100 oC above ambient atmospheric atmospheric temperature. temperature, and the wind speed is determined The wind sensor control circuit requires by measuring the power needed to maintain the information about the ambient atmospheric temperatures, so that it can maintain an over- hot wire at this temperature. The wind direction o is determined by TC’s that detect the heated temperature of 100 C. For MVACS, this data plume blown downstream from the hot wire. was provided by a TC mounted directly below The wind sensor uses a pair of hot wire the anemometer (Fig. 18). For NetLander, this elements that are connected in parallel to information will be provided by a pair of TC’s provide redundancy. Each element is a 10-mm that are mounted between the wind sensor support disks, just outside of the direction TC’s long, 12.5-mm diameter, ~10 ohm, Platinum- o Iridium wire that is wrapped loosely around a (Fig. 19). Two TC arrays mounted 180 apart 50-75-mm diameter thread consisting of ~10 will be used to insure than one is always strands of 25-mm diameter Kevlar fiber. The upstream, and not contaminated by the warm entire strand is then coated with a thin (<25 plume.

NetLander ATMIS: Mars Meteorological Network 22 ATMIS: Mission Description ATMIS will acquire data during the cruise, entry, descent, and landed phases of the NetLander Mission. During cruise, health checks will be performed monthly to monitor the vacuum calibration of each instrument. During entry, accelerometers and gyros in the EDLS will collect data that will be used to derive the atmospheric structure at altitudes between ~150 km and the surface. After landing, the surface weather instruments will make time-resolved meteorological Fig. 19: Top view of wind sensor, showing measurements from the 4 different landing placement of central hot wires, surrounding sites. These data will be collected throughout direction TC’s and the ambient temperature the Martian day for up to one Martian year. TC’s. As the wind blows across the hot wires, the heated plume is detected by the ATMIS: Data Acquisition, Analysis direction TC that is downwind. One of the 2 and Archiving ambient temperature TC arrays is always upwind. Retrieving the Atmospheric Structure: The NetLander EDLS accelerometers will measure For MPL MVACS, extensive tests of this the deceleration along three Cartesian axes. The 17 gram wind sensor were conducted in the Mars Pathfinder ASI software (Magalhães et Mars Aeolian Facility at NASA Ames (with al., 1999) will be modified to retrieve density blowing dust), and Mars chambers at JPL. and temperature profiles from these data. These tests confirmed that it was both robust These modifications will incorporate gyroscope and reliable, producing accuracies of ~10% at data in the analysis to provide additional wind speeds between 0.1 and 100 m/sec at information on absolute angular orientation of Mars-like pressures and temperatures. The the lander. This new information will be most circuit delivers 0.05 to ~140 mA (at ~1 volt) as valuable during the parachute phase, allowing the wind speed increases from 0 to ~100 m/s. atmospheric structure retrievals below ~10 km. If one of the two hot wire elements is broken, EDLS sampling will begin before the the maximum current decreases to ~108 mA, expected atmospheric entry to verify the zero but the sensor continues to function. offset of the instrument. The ~500 s entry, descent, and landing sequence will produce Wind Sensor Data Rates: Like ~768 kbits of data. For Pathfinder-like entry temperatures, wind velocities must be sampled conditions, this sampling frequency implies at 0.2 to 1 Hz to resolve convection, dust vertical sampling resolutions of <60 m and devils, and other rapidly varying phenomena. horizontal sampling resolutions of <250 m. Each wind sample includes the hot wire voltage After landing, a full error analysis will be and current, 2 ambient TC’s, and 10 outputs conducted including uncertainties in entry from the 20 direction TC arrays. If each of velocity, instrument performance, and these 14 values is digitized with a 16-bit ADC aerodynamic coefficient. External constraints and sampled at 1 Hz, the data rate would be on the landing sites derived by Doppler 224 bps. If the wind direction is determined on tracking of the radio signal from the probes, board, each sample includes only 5 words, and descent velocities from their radar altimeters, the data rate falls to 80 bps for 1Hz sampling. and ATMIS surface meteorology observations For this case, if ATMIS collects data for 5- will also be used to validate the entry profiles. minute periods at 1 Hz every 30 minutes (25 The structure of the EDLS density, periods/Sol), the total data volume would be pressure, and temperature profiles will be 600 kbits/Sol. These data can be calibrated on compared to predictions from the NASA Ames board and averaged over 5-minute intervals or Mars General Circulation Model (MGCM) and the raw data can be returned directly to Earth. previous ASI profiles from Viking and MPF. Linear analytical wave theory will be applied to

NetLander ATMIS: Mars Meteorological Network 23 determine if any periodic structures found in software uses algorithms and calibration the profiles could be atmospheric waves. coefficients derived from pre-launch testing to provide a near real-time conversion of the raw Surface Temperature and Wind Data data from these instruments into geophysical Acquisition and Analysis: Instrument health quantities (i.e., time-varying temperature, checks will be performed monthly during the vertical temperature gradients, wind speed and cruise phase to monitor the performance of the direction). These data will be combined with ATMIS instruments. During surface ATMIS pressure, humidity, and surface operations, ATMIS data rates and data volumes temperature data to derive hourly-averaged will be variable. Data will usually be collected heat, momentum, and moisture fluxes. They in 1 of 3 surface sampling modes. In Mode 1, will also be combined with ATMIS dust optical pressure, humidity and dust optical depth will depth and Electric Field (ELF) measurements be sampled at 30 minute intervals throughout to identify correlations among these quantities the day, yielding 50 samples/sensor/Sol. Wind that might provide insight into the physical and temperature data will be sampled at 0.2 or mechanisms that levitate and transport dust. 1 Hz for 5 minute periods to resolve the rapid variations associated with convection and other The GCM Modeling Task: The key phenomena, such as dust devils. Mode 1 data measurements needed by the MGCM are the will be calibrated on board. For each 5-minute atmospheric structure, dust optical depth, and session, the averages, minimums, and surface pressure. The dust optical depth will be maximums of temperature, its vertical gradient, used to prescribe the atmospheric forcing, and wind speed, and wind direction will be the model will be used to predict the returned, along with the horizontal heat and atmosphere’s response, which can be validated momentum fluxes. The total Mode 1 data through comparisons with observed pressures, volume is ~1 Mbit/Sol. temperatures and winds. Once a good fit is ATMIS also has “scan” and “burst” modes achieved, the model will provide a physical (Modes 2 and 3), which sample the sensors basis for extrapolating the ATMIS data to the continuously for fixed periods, (e.g., 1 hour) global-scale wind systems. and return raw data to Earth. These high- resolution modes will allow estimation of ATMIS Data Release and Archiving: The boundary layer parameters (Tillman et al., NetLander data will be released to the 1994), record transient events including dust international scientific community after a devils and extreme winds, and facilitate the calibration/validation period of less than six verification of sensor performance. Modes 2 months of receipt by the PI’s. Scientific results and 3 will return 0.3-1Mbit/hour. from NetLander will be made available through The atmospheric temperature and wind data publication in appropriate refereed journals or will be processed using updated versions of the other established channels of communication. MPL MVACS Met Station software. This Final release of validated data in PDS- approved format will be done within 6 months Table 12. Level 0 ATMIS Data Products Data Product Sample Rate Description 3-axis Accel 32 Hz Output from EDLS 3-axis descent accelerometers EDLS 3-axis Gyro 32 Hz Output from EDLS 3-axis gyros Top TC 0.2 - 1 Hz TC Voltage near top of ATMIS/ELF Boom Middle TC 0.2 – 1 Hz TC Voltage near middle of ATMIS/ELF Boom Atmospheric Bottom TC 0.2 - 1 Hz TC Voltage at bottom of ATMIS/ELF Boom Temperature IB PRT V 0.2 – 1 Hz Isothermal Block Reference PRT voltage IB PRT I 0.2 – 1 Hz Isothermal Block Reference PRT Current Ref TC 0.2 – 1 Hz Voltage for zero-point TC on IB PRT Hot Wire V 0.2 – 1 Hz Hot Wire Voltage Hot Wire I 0.2 – 1 Hz Hot Wire Current Wind Velocity 10 Dir TC’s 0.2 – 1 Hz 10 voltage differences for 20 directional TC arrays ATM-TC1 0.2 - 1 Hz TC voltage from Ambient Temperature TC 1 ATM-TC2 0.2 - 1 Hz TC voltage from Ambient Temperature TC 2 NetLander ATMIS: Mars Meteorological Network 24 of data acquisition. A data dictionary Dr. Robert Haberle is a Research Scientist conforming to PDS standards will be in the Space Science Division of NASA/ARC. developed, and each product will be formatted During the NetLander implementation phase, according to the latest PDS usage. Data will be Dr. Haberle will participate in all ATMIS put on-line on WWW servers. Data will also be Science Reviews. He will assist in the distributed on CD-ROMs or the corresponding development of sampling strategies and technology in the 2005 – 2007 timeframe. calibration activities, and will provide inputs as needed for site selection to optimize the science ATMIS: Science Team return for global scale meteorology objectives. ATMIS has an international team lead by During mission operations, he will provide Ari-Matti Harri of the Finnish Meteorological results from his general circulation model to Institute (FMI). The ATMIS team includes 4 help interpret the data and revise sampling Co-PI’s who will provide instruments or strategies. He will be funded by NASA. subsystems for this experiment. Dr. David Dr. Julio A. Magalhães is a NASA/ARC Crisp will provide the atmospheric temperature Research Associate, through a Cooperative and wind sensors for ATMIS. The Science Agreement between San Jose State University Team also includes 3 other U.S. Co- Foundation and ARC. He specializes in the Investigators: Dr. Robert Haberle, Dr. Julio observational characterization of thermal Magalhães, and Prof. James Tillman. structures and dynamics of planetary Mr. Ari-Matti Harri is the leader of the atmospheres. He was the lead investigator on Mars Exploration Group of the Finnish the Atmospheric Structure Investigation (ASI) Meteorological Institute/Geophysical Research for the MPF ASI/MET experiment. He was (FMI/GEO). He was a Co-I for Cassini also the member of the Mars Microprobe Huygens HASI and MPL MVACS payloads Science Team and the MPL Participating and was a member of the IMEWG. As PI of Scientist responsible for the analysis of ATMIS, he will be responsible for the accelerometer data to reconstruct atmospheric development, integration, test, and calibration structure profiles. Dr. Magalhães will perform of the ATMIS experiment. He will lead the all tasks related to the analysis of ATMIS reduction and validation of ATMIS data, and atmospheric structure profiles. He will be will be responsible for archiving these data. His funded by NASA. participation is funded by FMI. Prof. James E. Tillman is a Research Dr. David Crisp is a Senior Research Professor in the University of Washington Scientist at JPL/Caltech. He was a member of Atmospheric Sciences Department. He the MPF ASI/Met Science Team, and was specializes in boundary layer meteorology on responsible for the MPL MVACS MET Earth and Mars. He was a member of the Package. The proposed ATMIS TC’s and wind Viking Meteorology Science Team, and a sensors evolved from that effort. As an ATMIS member of the MPF ASI/Met Advisory Group. Co-PI, Dr. Crisp is responsible for the He has more than 25 years of public outreach development, integration, test, and calibration experience. For ATMIS, Prof. Tillman will of the atmospheric temperature and wind work with Dr. Crisp to develop, test, and sensors. He will also lead the reduction and calibrate the wind and temperature sensor validation of wind and temperature data, and systems. Prof. Tillman will analyze ATMIS will be responsible for archiving these data. He data to study Kelvin modes, annual pressure will be funded by NASA. cycles and unstable conditions to validate Dr. Simon Calcutt is the head of Planetary methods for determining heat flux. He will be Experiments at Oxford University, UK. He funded by NASA. was a Co-I on MO/MCO PMIRR, Galileo NIMS, and the Cassini CIRS instrument. For NetLander, he is the ATMIS Co-PI responsible for providing the ATMIS/ELF boom. He will integrate the JPL-supplied instruments on that boom and assist in the analysis of the ATMIS temperature and wind data. His contributions will be funded by Oxford University.

NetLander ATMIS: Mars Meteorological Network 25 EDUCATION/PUBLIC OUTREACH NetLander Project Overview Table 13: NetLander Outreach Budget The Mars NetLander mission (see follows AO Outreach costing guidelines MoO Cost Cap $35M Summary, below) is a European project, with U.S. participation cost $34.2M U.S. participation proposed as a Discovery Outreach costs $0.68M Mission of Opportunity (MoO). Outreach for Percentage 2% of mission cost the U.S. participation in the project is proposed here and adheres to the AO costing guidelines Roles and Responsibilities of 1-2% of the proposed costs (Table 13). Coordinator and Science Team member Jim Tillman will have final responsibility for the NetLander Outreach Abstract effectiveness of the Outreach Program (Fig. The NetLander E/PO program will build 20). As an invited Co-Investigator and Member upon the effective “Live from Earth and Mars” of the FMI ATMIS Team, his NetLander outreach program developed at the University outreach proposal component was accepted and of Washington. It will team scientists with local is an integral component of the mission (see educators to develop curriculum supplements MoU and Letter of Collaboration). It covers based on NetLander investigations. Emphasis student participation in the mission, developing will be placed on choosing educators from educational resources and web sites to present schools in traditionally underserved these and “Live from Mars” weather in the US communities. Partnerships with groups such as and Finland. The ATMIS Modules and web JPL’s Mars Outreach Office, the NASA Space sites proposed here will be developed at Grant Program, and SpaceLink website will be University of Washington (UW) under his used to expand the scope of these efforts. direction, taking advantage of his overall Ongoing evaluations will be used to enhance program and in collaboration with Co- the materials and increase their effectiveness. Investigator David Crisp. SEIS and NEIGE Our approach is to develop two one-week Modules will be developed at JPL under the modules per experiment over the course of the direction of Principal Investigator Bruce effort. These materials could be used Banerdt and Co-Investigator Bill Folkner. For independently to fit schedules and needs. SEIS and NEIGE, JPL’s Mars Outreach Program will coordinate the development effort. This coordination will include recruiting qualified educators and pairing them with curriculum development experts at JPL’s Educator Resource Center to facilitate the production of materials that adhere to current educational standards, as well as assisting with effectiveness evaluations for schools in the local area. Jim Tillman and associated NetLander Mission Summary: educators will develop a website at UW for the Four NetLanders will be built by a European distribution of NetLander E/PO materials for consortium and integrated onto an orbiter all three instruments and will distribute the launching in June, 2005. Three experiments lesson plans to US and Finnish educators with US components are proposed for through his existing network of contacts. He inclusion in the NetLander mission: the SEIS will also hire a professional evaluator to plan seismic and ATMIS meteorological the evaluations of effectiveness for schools in experiments will be integrated into each the UW area, in collaboration with a similar lander, and the NEIGE geodesy experiment effort by JPL’s Mars Outreach Program. will use hardware on the orbiter and landers ATMIS Plan: The ATMIS outreach to measure subtle changes in Mars’ rotation. program will build on Jim Tillman’s prior This lander network will make global climate experience including his Viking and the and internal structure measurements of Mars Pathfinder-based "Live from Earth and Mars" possible for the first time.

NetLander Mars Science Network 26 about local seismic Activity Name Start Date Finish Date 2001 2002 2003 2004 2005 2006 2007 2008 hazards such as Set up facilities and support at UW 4/1/01 1/31/02 Develop ATMIS lesson 1 (UW) 6/1/02 10/1/02 Pilot and Revise ATMIS lesson 1 (UW&JPL) 9/1/02 9/1/03 earthquakes (in southern Test and Evaluate ATMIS lesson 1 (UW&JPL) 10/1/03 5/31/04 Develop NEIGE lesson 1 (JPL) 6/1/03 10/1/03 CA) and earthquakes and Pilot and Revise NEIGE lesson 1 (UW&JPL) 9/1/03 9/1/04 Test and Evaluate NEIGE lesson 1 (UW&JPL) 10/1/04 5/31/05 volcanoes (in WA). This Develop ATMIS lesson 2 (UW) 6/1/04 10/1/04 Pilot and Revise ATMIS lesson 2 (UW&JPL) 9/1/04 9/1/05 Test and Evaluate ATMIS lesson 2 (UW&JPL) 10/1/05 5/31/06 material could be made Develop SEIS lesson 1 (JPL) 6/1/05 10/1/05 Pilot and Revise SEIS lesson 1 (UW&JPL) 9/1/05 9/1/06 appropriate for students Test and Evaluate SEIS lesson 1 (UW&JPL) 10/1/06 3/31/07 Develop NEIGE lesson 2 (JPL) 6/1/06 10/1/06 in 5th-6th grade, while Pilot and Revise NEIGE lesson 2 (UW&JPL) 9/1/06 6/1/07 Test and Evaluate NEIGE lesson 2 (UW&JPL) 10/1/07 3/31/08 older students (post Develop SEIS lesson 2 (JPL) 7/1/06 10/31/06 Pilot and Revise SEIS lesson 2 (UW&JPL) 12/1/06 9/30/07 Test and Evaluate SEIS lesson 2 (UW&JPL) 12/1/07 5/31/08 Earth Science) could Distribution of tested and evaluated lessons 6/1/04 9/30/08 2001 2002 2003 2004 2005 2006 2007 2008 learn about the Fig. 20: Activities build awareness prior to landing in 2006, implications of encouraging interest during mission operations. During piloting and seismology for the revision, improvements will continually be evaluated for content, interior structure of standards, and applicability and will be incorporated as appropriate. terrestrial planets. Dr. Banerdt, the PI for the (LFEM) outreach programs, which compare NetLander Proposal, and Co-PI for SEIS, will Pathfinder temperatures with Viking and Earth. be responsible for ensuring that the Summer These materials will be created and evaluated Education Fellow receives guidance on content by Prof. Tillman and experienced teachers; for a one week lesson plan based on Martian these initially will be targeted for grades 5-8. and terrestrial seismology. This guidance will They will complete the development, piloting, include suggestions on reading material, and distribution of the first of a suite of websites, and contacts for research into “Temperature of Earth and Mars” (TEM) seismology and its implications for modules where students make hands-on understanding the Earth and Mars. measurements with the same type NEIGE Plan: The goal of NEIGE outreach thermocouple temperature sensors used by will be to communicate the role of geodesy in Viking, Pathfinder, and NetLander. By understanding the internal structure and comparing their data with those from the evolution of terrestrial planets, as well as the missions, and with observations from their atmosphere-surface interactions that affect the research-quality school weather stations, length of day. This material would be most students develop insights into fundamental appropriate for students who have already had physical concepts such as temperature-energy Earth Science. Dr. Folkner, the co-investigator relationships. Recently, 4th grade students have for NEIGE, will be responsible for ensuring measured sensor time constants and explored that the Summer Education Fellow receives errors caused by sunlight heating the sensors. guidance on content for both terrestrial and Schools without their own weather stations can Martian geodesy studies. This guidance will participate by tracking data posted to the TEM include suggestions on reading material, website. As an invited Finnish Meteorology websites, and contacts in the terrestrial and Institute (FMI) ATMIS team Co-Investigator, Martian geodesy community. Prof. Tillman has accepted an offer of support from Prof. Risto Pellinen to develop a outreach NetLander Outreach Program program in Finland as a Visiting Professor at addresses Discovery E/PO goals FMI. Materials developed by his US-Finnish 1. The quality, scope, and realism of the collaboration will be adapted for use in this proposed E/PO program including the U.S. outreach component. These coordinated adequacy, appropriateness, and realism of the efforts in the US and Finland will feature proposed budget internet-based collaborations between students Sharing our activities and results through in these two countries, further motivating their education and public outreach are essential interest in science and math. goals for the NetLander Team. Accomplishing SEIS Plan: The goal of the SEIS outreach this within 1-2% of our mission cost is a program will be to develop lesson plans based challenge – one we plan to meet by taking on seismology investigations on the Earth and advantage of the existing infrastructure Mars, tying this material to student concerns developed by JPL’s Mars Outreach Office and

NetLander Mars Science Network 27 Jim Tillman at UW. Due to our limited for activities such as writing software, resources, we plan to pilot our educational analyzing results, helping develop the "Viking modules in areas local to the science team View of Mars" exhibit at the Smithsonian members, and expand their scope through National Air and Space Museum, and cooperation with the NASA Solar System developing the Pathfinder LFEM website and Educators Program and distribution sites such outreach program. Currently, a “Temperature as NASA SpaceLink. The experience of our of Earth and Mars” (TEM) educational module Outreach Coordinator Prof. Tillman in is being developed and piloted, funded by a gift developing materials for students of all ages from Jeremy Jaech, a former employee who and engaging them in scientific investigations worked on Viking Mission Operations will be critical to the development of an programming for Prof. Tillman. effective program. The proposed NetLander 3. The establishment or continuation of outreach program provides a unique effective partnerships with institutions and/or opportunity for students of all ages to personnel in the fields of education and/or participate in space science research, and to public outreach as the basis for and an understand its value “close to home”. integral element of the proposed program 2. The capability and commitment of the The NetLander Outreach Program will take proposer’s team and direct involvement of one advantage of ongoing E/PO efforts. These or more science team members in overseeing include Prof. Tillman’s FMI contract to set up and carrying out the proposed E/PO program NetLander ATMIS outreach program in The NetLander Outreach Program has Finland and in the United States (see MoU), strong support from the Science Team. The with a web interface reporting data live from Coordinator, Prof. Tillman, also an FMI Mars, and his work installing weather stations ATMIS Science Team member, has over 25 at schools in the Seattle area, with web-based years of experience in Public Outreach efforts, data reporting for comparison of current dating from his pioneering Viking mission to terrestrial with historical and future Martian Mars science and outreach programs. Co- weather. Additional schools, from elementary Investigator Dr. David Crisp is a certified to high school, will be added to the network. In secondary education teacher with a B.S. in conjunction with the undergraduate Electrical Educational Curriculum and Instruction. The Engineering Department (See UW EE Chair NetLander Discovery Proposal PI and Co-I’s Chizeck’s letter) and other students, Grade 9-12 will be involved in the Outreach efforts students will be trained to fabricate, test, and pertinent to their instruments, giving educators enhance our temperature systems, and to direct experience with working scientists. assemble, install, maintain, and program the Prof. Tillman’s leadership will benefit weather stations. They and students in grades NetLander Outreach by taking advantage of his 5-8, will be given opportunities to participate in network of committed partners in the education experiments such as comparing rainfall at and public service community. For example, nearby schools. JPL’s Office of University Rotary has provided matching funds Communication and Education has several for a research-quality weather station at ongoing programs to which we plan to submit McClure middle school and a portable material, including Project ALERT, a pilot demonstration - calibration weather system. In program between NASA and California State addition to his experience developing University system to address the state of Earth educational materials and presenting science science education of future K-12 teachers. results to students of all ages, he has Another example is the “From the Outer incorporated high school and undergraduate Planets to the Inner City”, which reaches students into his Viking, Mars Pathfinder, and teachers in traditionally underserved schools in NetLander programs. They have been essential the LA area. We can expand outreach efforts by

"A good understanding of science is fundamental to being a good citizen and to being productive in the information economy of the future. Science and math education for our children is therefore vital to their success. In this age of computers and video games, if our kids are to be attracted to science and math, we need to serve it up to them in ways that capture their attention and imagination. What Jim Tillman is doing with Mars weather to teach science concepts to young students is a good example of this, and is the reason I have supported him on this project." Jeremy Jaech, Founder and CEO of Visio (a Division of Microsoft); Engineering VP and a founding member of Aldus

NetLander Mars Science Network 28 taking advantage of these ongoing programs for Educator Outreach Center for assistance in a minimal investment ($3-5K/year). developing science outreach materials. 4. The adequacy of plans for evaluating 6. The degree to which the proposed E/PO the effectiveness and impact of the proposed effort contributes to the training of education/outreach activity. underserved and/or underutilized groups and It is critical that evaluation efforts reveal their involvement in and broad understanding lessons learned, and determine whether the of science and technology proposed E/PO program meets the stated goals To reach underserved students, we will and objectives and/or had other unanticipated recruit educators from underserved effects. To this end, we will take advantage of a communities for our education fellowships. comprehensive outreach evaluation program Based on their experience, JPL's Mars being developed at JPL. JPL is also Outreach Office and Prof. Tillman’s local establishing long-term relationships with colleagues will help identify qualified educators through their “Solar System Educator candidates. Prof. Tillman already has a formal Program”. Educators make a commitment to collaboration with Seattle’s McClure Middle hold teacher training workshops in their own School, which serves a diverse student communities, and can provide feedback on how population; (see attached MoU and Letters of materials are working in the classroom. As part Support from Principal Phil Brockman and of his local outreach effort, Prof. Tillman will Math Curriculum Specialist Judy Slattery). hire a certified evaluator to help in the planning 7. The potential for the proposed activity to of the program and possibly its execution and expand its scope by having an impact beyond final evaluation who will be assisted by a the direct beneficiaries, reaching large graduate student; the results will be published audiences, being suitable for replication or and used to enhance the existing materials, and broad dissemination, or drawing on resources those developed in later stages of the program. beyond those requested in the proposal 5. For proposals strongly affecting the formal We will draw on existing contacts and education system, the degree to which the resources such as NASA’s Space Grant proposed E/PO effort is aligned with Program and JPL’s Mars Outreach Office to nationally endorsed education reform efforts maximize the effectiveness of the NetLander and/or reform efforts at state or local levels outreach effort. Our first step will be to develop By gathering, recording, representing, and displays for JPL's open House, attended by interpreting quantifiable data from both over 50,000 visitors each year for the past schoolyard investigations and from the Web, several years. JPL has sent these materials to students involved in NetLander outreach will local museums, such as the California Science engage in inquiry science that follows the Center, to reach communities unable to attend process and content standards suggested by Open House. Impact of these displays will be both the National Research Council National enhanced by seminars and curator training Science Education Standards, and the programs. Prof. Tillman’s experience securing Washington State Essential Academic Learning E/PO funding and resources from a variety of Requirements in Science. Even more public and private sources will be invaluable important, our program stimulates students and for expanding impact of the program. In an teachers to move beyond the standards, attached letter, Dr. Tom Watters of the capturing their imaginations and generating the Smithsonian National Air and Space Museum kinds of questions that drive scientific inquiry. has expressed interest in a NetLander exhibit Our Summer Education Fellows will be chosen based on Tillman’s previous development of from master educators intimately familiar with the permanent (1983 to present) “Viking View current educational standards and reform of Mars” exhibit and “Live from Mars” efforts, using their experience to develop lesson Pathfinder exhibit. By drawing on current and plans based on NetLander instruments and past experience, and both private and public observations and on Earth analogs. Educators funding, we will reach a far broader audience will work with science team members to than our Pathfinder LFEM web program (> develop materials to integrate into their classes, 2,000,000 different web viewers, July 1997), and can take advantage of experts at JPL’s with Mars NetLander results.

NetLander Mars Science Network 29 NEW TECHNOLOGY TRANSFER As a product of the proposed investigation, monitoring and control. This range of the NetLander team will work with the JPL applications makes this component an excellent Technology Commercialization Office to candidate for technology transfer. transfer the JPL-developed wind sensor If this proposal is selected through this AO, technology described above to private industry. JPL will initiate the formal technology transfer For MPL MVACS, the control and readout process. electronics for the wind and temperature sensors were designed, manufactured, and qualified by JPL personnel. As we noted above, these electronics must be repackaged for NetLander to reduce their size, mass, and recurring cost. This will be accomplished by integrating the hundreds of discrete components in the wind sensor control circuit into a custom analog Application Specific Integrated Circuit (ASIC). This ASIC will then be combined with the temperature sensor readout electronics in a custom Multi Chip Module (MCM). The wind sensor ASIC must be fabricated by an outside company, and it is likely that the MCM will be as well. Hence, even though the use of these advanced packaging techniques introduces little risk, this approach provides an opportunity to infuse these NASA-developed technologies into the commercial sector. With their reduced size, mass, power consumption, and recurring cost, the proposed wind and temperature sensor electronics should be very attractive for use on future Mars landers. These characteristics would make them especially appropriate for small landers, such as Scouts. The compact, low-power wind sensor control ASIC could also be used in a broad range of scientific applications that employ conventional constant over-temperature hot-wire/hot-film control techniques. These include thermal anemometers for terrestrial boundary layer and wind tunnel studies, as well as thermal cloud liquid water sensors. The high degree of integration and environmental tolerance of the proposed ASIC, combined with its (expected) low recurring cost, would also make it attractive for use the broad range of industrial processes that require flow

NetLander Mars Science Network 30 SMALL DISADVANTAGED BUSINESS PLAN JPL Support for SDB Participation: Despite an uncertain business environment, JPL strongly supports NASA's JPL has set ambitious goals for small socioeconomic development programs, and disadvantaged business participation. Goals and makes an aggressive effort to assist the agency performance against these goals for FY00 are in meeting its goals for participation of Small shown in Table 14 below. Disadvantaged Businesses, Women-Owned NetLander SDB Participation: Businesses, and Historically Black Colleges The Mars NetLander Project has set a goal and Universities and Minority Institutions of 25% SocioEconomic business participation (HBCU/MI). JPL has a committed Small in all out-of-house contracted work, consistent Disadvantaged Business Program administered with JPL’s achievements in this area over the by the JPL Business Opportunities Office. past several years. Several eligible vendors JPL meets its goals with systematic have already been identified. The ATMIS planning that sets goals at the program office sensor is based on previously-flown designs and technical division level, tracks progress, which incorporated materials and parts from at and implements programmatic actions. least two SDB's: Southern California Metals Progress is reviewed in biweekly status Joining (thermocouples) and Laguna meetings with each Technical Division Small Components (electronics components). Business Representative conducted by Mr. Mel The ATMIS Instrument Manager is pleased Roberts, Principal, Acquisition Operations and with these companies' past performance, and is Planning. committed to working with them again to build JPL has been widely recognized for its the NetLander ATMIS instruments proposed leadership in the area of SDB participation. In here. The NEIGE and SEIS instruments will 1995, JPL was awarded the U.S. Small take advantage of JPL's SDB-participation Business Administration's Award of infrastructure. We plan to draw from JPL's list Distinction, and in 1996, was presented with of qualified Small Disadvantaged Businesses the SBA's highest and most prestigious award, for procurement and manufacturing of parts the Dwight D. Eisenhower Award for and materials. The Project Manager and Excellence. The award recognizes large prime Instrument Managers will work with the JPL contractors that have excelled in their use of Business Opportunities Office to identify small businesses as subcontractors. JPL was specific matches between NetLander needs and judged the most outstanding of all research and the capabilities of candidate businesses. development companies in the SBA's portfolio Oversight of SDB implementation is assigned of 2500 large contractors. to each Instrument Manager (IM). Specific In 1997, the National Association of Small duties include the development, preparation Disadvantaged Business (NASDB) recognized and execution of subcontracting plans and JPL's Thomas May as Advocate of the Year for tracking implementation achievements and his outstanding efforts in support of minority- accomplishments of the goals for the project. owned businesses; in 1998, Larry Dumas, JPL Deputy Director, was named CEO of the year. Table 14: JPL’s Proven Record for Subcontracting Awards, in $M and (% of subcontracts) FY95 FY96 FY97 FY98 FY99 Small 150 (35%) 190 (39%) 213 (36%) 214 (34%) 232 (35%) Small Disadvantaged 62 (15%) 85 (17%) 86 (15%) 88 (14%) 118 (18%) Woman-Owned 15 (4%) 24 (5%) 37 (6%) 28 (4%) 25 (4%) Socioeconomic 78 (18%) 106 (22%) 120 (20%) 112 (18%) 161 (24%) *Socioeconomic Business includes SDB, WOB, HBCU/MI and subcontract flowdown.

NetLander Mars Science Network 31 MISSION IMPLEMENTATION Mission Programmatic Description maintaining clear technical and management A consortium of international agencies is interfaces to minimize management complexity responsible for implementing the NetLander and risk. Risks and benefits of the proposed mission. It is managed by the Centre National cooperative arrangement as well as d'Etudes Spatiales (CNES) of France, which management approaches to mitigating these will have overall responsibility for mission risks are discussed further in the Management success. The Principal Investigator of this Section. Information related to the proposed proposal, Dr. Bruce Banerdt, is responsible for instruments’ requirements on and interfaces the overall success and scientific integrity of with the sponsor’s instruments/spacecraft U.S. contributions to the NetLander mission follow in sections specific to each U.S. and is the final project authority on all issues contribution. related to those contributions. To execute that NetLander DataPolicy responsibility, the PI has established the The NetLander data policy will be NetLander project as an integrated partnership established following the terms of the among the U.S. Co-I’s for SEIS, NEIGE, and Memorandum of Understanding (MoU) to be ATMIS. In addition to his PI role, Dr. Banerdt signed by the NetLander Consortium members will lead the development and data analysis and the MoU to be signed between CNES and efforts for the SEIS instrument. Dr. William NASA. It is anticipated that the NetLander data Folkner will lead the NEIGE effort, while Dr. policy will comply with the following general David Crisp will lead the effort for ATMIS. terms: Each was named as a Co-PI in the European · Scientific results from NetLander scientific NetLander proposal, and has teamed with an data will be made available to the general Instrument Manager chosen for their scientific community through publication in experience in the design and development of appropriate refereed journals or other the proposed instruments. established channels of communication. Such This approach maximizes the scientific, publications and reports will include a suitable technical, and financial benefits offered to all acknowledgement of the services afforded by partners by international cooperation while the NetLander Consortium.

NetLander Mission Overview Four NetLander spacecraft will be built by the NetLander Consortium, under the leadership of CNES. The landers will be integrated onto a CNES communications orbiter and launched aboard an Ariane 5 in June 2005. Three U.S. experiments are proposed for inclusion in the NetLander payload: the SEIS seismic experiment and the ATMIS meteorological experiment will be integrated into each lander, and the NEIGE geodesy experiment will be placed on the orbiter. Prior to entering orbit, the four landers will be released and enter the Mars atmosphere, where atmospheric structure measurements are made during the Entry and Descent phases. Each lander will land in a location selected by the Science Team, using a Mars-Pathfinder-style airbag landing. The landing will be followed by deployment of the lander’s experiments and solar panels. Lander and orbiter operations will comprise a full Martian year of measurements by the first network of science stations on Mars.

NetLander Mars Science Network 32 · The PIs will provide timely updates of their Reliability of the U.S.-provided NetLander investigations’ results to the NetLander instruments will be achieved through the Consortium in a format suitable for inclusion in selection of electronic parts based on online electronic forums maintained by the established criteria appropriate to the project members of the NetLander Consortium. characteristics including mission duration and · NetLander scientific data will be released to expected radiation environments. Reliability the international scientific community by analyses consisting of worst case analyses, Investigators after a calibration/validation interface Failure Modes Effects and Criticality period of no longer than six months. The six- Analyses (FMECAs), and parts stress analyses month period begins with the receipt by the PIs will all be performed per a planned reliability of the data and any associated spacecraft data assurance plan. Fault tree analyses (including in a form suitable for analysis. At the end of system analyses conducted in conjunction with this period, the NetLander scientific data will systems engineering), FMECAs, and become publicly available. probabilistic risk analyses will be used to assist · All PIs will share NetLander scientific data, in decision making trade studies as appropriate. under procedures defined by the NetLander PIs The analyses performed on flight hardware team, to enhance the scientific return. designs from predecessor projects will be · The NetLander Consortium will work to assessed for their applicability to this project. ensure that all Investigators have access to Environmental design and testing will utilize other NetLander science and engineering data robust margins appropriate to the project relevant to the calibration/validation of that characteristics. These requirements will Investigator’s investigations. include, as a minimum, dynamics, thermal vacuum, Electromagnetic Compatibility Safety and Mission Assurance (EMC), and natural space radiation. Quality A comprehensive System Safety and assurance will provide inspection of key Mission Assurance (SMA) program, extending operations as well as process verification. throughout the project lifecycle, will be Software quality assurance will provide developed based on processes and procedures software development support tailored to the that exist within JPL and its European partners. project software requirements. Software The NetLander Consortium, under the Independent Verification and Validation leadership of CNES, will have the primary (IV&V) will be based on an assessment of the management and oversight of the integrated project software requirements and functions. program. JPL will develop instrument safety The SMA program will be managed and and mission assurance plans in collaboration implemented by a staff with direct with the NetLander Consortium. The JPL administrative line management independent of NetLander Mission Assurance manager, in the project line management. The staff will be conjunction with the NetLander Instrument assigned to the project team as safety and Managers, will ensure that all processes and mission assurance technology providers. Risk procedures to be used on the project for assessments of each instrument from the safety systems safety and mission assurance will be and mission assurance staff will be reviewed and assessed early in the formulation accompanied by its recommendations for risk phase of the project relative to the mission mitigation. characteristics. Suggestions for changes will be SMA will support a risk management made as necessary to the NetLander project. program designed to identify, manage, and The SMA program will include mitigate risks existing on the project. It will management, reliability engineering, also support a comprehensive project review environmental requirements engineering, process to ensure that the safety and mission electronic parts engineering, hardware and assurance program is thoroughly reviewed and software quality assurance, and materials and assessed throughout its lifecycle. contamination control. JPL and the NetLander The SMA program will comply with JPL’s Consortium will each provide safety and ISO 9001 requirements. The program will also mission assurance functions to the project in a integrate lessons learned from past projects into teaming manner that ensures technical strength its implementation along with JPL design and in all of the disciplines identified above. operations principles.

NetLander Mars Science Network 33 SEIS: General Mission Information Table 15: SP Sensor Performance. -8 2 The SEIS instrument package uses both Sensitivity Better than 10 m/sec /ÖHz long and short period sensors. Two very- over entire band -9 2 broad-band Long Period (LP) seismometers Peak sensitivity 5x10 m/sec /ÖHz at 10 Hz will be supplied by CNES. They will provide Bandwidth 0.05 – 100 Hz a vertical output and one horizontal output with Preliminary finite-element analysis of the very high sensitivity and very low noise over a suspension has been performed, indicating that frequency band from DC to 5 Hz. Three broad- the design is free of spurious resonances within band, 2-axis, Short Period (SP) sensors will be the bandwidth. Before fabrication, a complete provided by JPL. One of these sensors will finite element analysis will be done to confirm provide the second horizontal component for the dynamics, including the absence of spurious the LP seismometers (along with a redundant resonances in the seismic bandwidth, and to vertical output), and the other two will confirm robustness to shock and model the comprise a complementary 3-axis seismometer temperature coefficients of the system. tuned to the frequency band 0.05 to 100 Hz. The proof mass, flexures, and moving This delivery will consist of two sets of sensor and actuator electrodes are patterned in engineering models, four sets of flight models, silicon using through-wafer deep reactive-ion and two spare sets. Each set is comprised of etching (DRIE). In order to maintain a constant one internal 2-axis assembly for mounting in fixed-plate/proof-mass separation, considerable the LP enclosure and two external 2-axis rigidity is required normal to the plane of assemblies for mounting on a spike. motion. Such flexure rigidity is achieved through careful design of the geometry SEIS: Characteristics and Fabrication combined with the large aspect ratio that can be The SP sensor consists of a micromachined produced by this micromachining process. suspension coupled to an ultra-sensitive The process flow for the production of the position transducer with analog electrostatic suspensions is shown in Fig. 22. Each feedback. The feedback signal is digitally fabrication run will produce a single set of converted to a serial-line signal which is sent to three 4-inch wafers – one spring/proof-mass the SEIS data acquisition electronics. The wafer and two capping capacitor plate wafers. anticipated sensor performance is shown in These three wafers will be bonded and diced to Table 15. produce twenty devices per wafer set. Two Suspension. The suspension (Fig. 21) will independent fabrication runs are scheduled be fabricated in the JPL Microdevices prior to delivery of the engineering models to Laboratory (MDL). The basic design evolved accommodate any minor design changes from a series of prototype microseismometers resulting from initial testing. Similarly, two produced in MDL. redundant fabrication runs are scheduled before

20mm

x

1mm Proof mass Fig. 22. Process flow for fabrication of springs microseismometer: (1) patterning and DRIE of top half of springs, (2) patterning and y DRIE of top capacitor plate structure, (3) DRIE of top capacitor gap, followed by bottom half of structure, (4) metallization of Fig. 21. Exploded cross-sectional view of capping wafers, and (5) bonding to form microseismometer structure completed structure.

NetLander SEIS: Mars Seismology Network 34 the flight model and spare delivery. The residual DC component of the Electronics. In parallel, the transducer deflection is separated from the seismic signal electronics will be designed and fabricated. The by the introduction of two distinct feedback transducer is based on a switched-capacitor paths, one carrying the high-frequency (HF) scheme already implemented and characterized signal that drives a weak actuator and the other at JPL for seismic applications. The transducer feeding a strong, levitating, low-frequency (LF) power has been measured at 2 mW. Amplifiers actuator. and switching elements for the transducer are A common drawback of levitating feedback available as radiation-hard, wide-temperature- systems is excessive noise from the voltage range devices. reference driving the LF path. By applying The feedback scheme (Fig. 23) separates feedback over a small portion of the full different amplitude and frequency domains of mechanical dynamic range of 1 g, this noise is the signal to relax the constraints for both the proportionately lower. In addition, this dynamic range of the electrostatic feedback reference noise is rolled off in the bandwidth of actuation and of the final digitizer. For large interest by a subsequent single-pole low-pass deflections, the proof mass is free to move passive filter. Furthermore, our design sums the open-loop and the motion is measured at a low LF and HF feedback forces at the electrodes resolution using a single overlapping electrode rather than at a summing amplifier, ensuring pair for tilt information. For smaller motions that no additional electronic noise is generated. feedback control levitates the proof mass by up Breadboard tests of this feedback scheme to ±0.02 g in each axis. The closed-loop demonstrate that the noise contribution of the response is flat over the seismic bandwidth for electronics will be considerable less than 1 this reduced dynamic range. To maintain a ng/Ö(Hz). linear response, two sets of selectable Prior to digitization, the seismic signal will electrodes offset by half the electrode period pass through a simple single pole-and-zero ensure that the feedback loop is always within band-pass filter for antialiasing, removing the the center half of the full range of the actuators. DC offset. An off-the-shelf 16-bit ADC This mixed open-loop, closed-loop scheme (AD7707 from Analog Devices, Inc), has been functionally reproduces, in a single selected that provides sufficient resolution in micromachined mechanism, the gross leveling our frequency band with a low power draw. and high-sensitivity feedback electronics of the This component is not available in a radiation- LP seismometer. In addition to reducing the hard model, although initial testing of this suspension noise, the lateral interdigitated Analog Devices series has indicated that the electrode geometry also allows for free motion design is not particularly susceptible to of the proof mass under full Martian and Earth radiation effects. Latch-up protection through gravity; the latter is imperative for ground power-supply monitoring will be utilized to testing. protect this critical component. Electronics will be fabricated on a single double-sided board. The board and sensor will be mounted on a baseplate compatible with the enclosure and spike materials to reduce thermal mismatch. In addition, the external sensors will be protected by a thin-walled enclosure provided by the French SEIS team. Software development for this sensor will be minimal. Communication will be over a three-wire serial line to the ADC to control channel, sampling rate and gain, and from the Table 16: SEIS SP Resources and Margins CBE Value Margin % Mass 50 gm 10 gm 20 Fig. 23. Feedback scheme for the Envelope 30x70x10 mm 10x15x10 >20 microseismometer. Power 40 mW 10 mW 25

NetLander SEIS: Mars Seismology Network 35 Planetary Protection. To satisfy planetary protection requirements, all NetLander components will be decontaminated during the integration process at CNES. Two methods are being considered. The first uses dry heat (105°C for 300 hours). The second employs chemical sterilization (hydrogen peroxide). Dry heat is the preferred sterilization method for the U.S.-supplied SEIS components. SEIS: Resources and Margins Table 16 lists the current best estimate of Fig. 24. Location of SP sensor within the mass, volume, and power for each sensor SEIS sphere. assembly, and margin against the allocation given to the SP sensors within the SEIS ADC returning the digital seismic signals. All package. The volume envelope is that of the time stamping and further processing will be most demanding location, inside the sphere. performed by the SEIS instrument electronics using routines developed by the French SEIS SEIS: Interfaces team. All interfaces for SEIS-SP are within the Environmental Testing. The batch SEIS instrument package; there are no direct fabrication of the suspensions will be exploited interfaces between SEIS-SP and the spacecraft. to provide good statistical confidence during Each SEIS package contains two LP sensors testing. The twenty nominally identical (provided by CNES), and one SP sensor suspension chips from each fabrication run will provided by JPL within a leveled sphere (Fig. be initially screened and candidates for each 24). A JPL 3-axis seismometer will be outside delivery selected. Component-level shock the sphere, attached to a fixture directly testing of the suspension mounted with the coupled to the surface. Each SP assembly will electronics on the baseplate will be completed be attached to its mounting point using a bolt at the predicted launch and landing loads for pattern in its base plate. The mounting fixtures the candidate sensor chips, and at considerable are the responsibility of the French SEIS team. margins for other chips selected for potentially The control and data acquisition electronics destructive testing. for the SEIS experiment will be housed in the Initial environmental testing of the lander’s temperature-controlled electronics integrated sensor assemblies will be performed box, which contains boards performing the in a small, dedicated vacuum chamber at JPL. following functions: interfacing with the Ambient vibration noise precludes the use of CDMS for power and data exchange (both conventional environmental chambers for such command and science data), communications testing. Two identical sensors will be tested with the LP and SP sensors, and data pre- using coincidence techniques to verify their processing and buffering. This equipment is the noise floor, and transfer functions will be responsibility of the Swiss SEIS team. Table 17 determined at room temperature for the describes the electronic interface. individual sensors. The units will be integrated with the complete SEIS package in France, and SEIS will subsequently be integrated with the NetLanders. The final transfer functions, Table 17: SP Electronic Interface which will be considerably different on the Connector 9 wires (per assembly) structure of the lander, will be determined in Power 3-wire power: ±15V, 5V, the mission configuration. During this GND integrated testing of the EQM system, the Comm 3-wire data: DIN/OUT, mounting scheme for the microseismometers SCLK, DGND will be optimized for sensor performance. 2-wire temp. (AD590): Temperature TEMP+, TEMP-

NetLander SEIS: Mars Seismology Network 36 NEIGE: General Mission Information NEIGE receiver design may be summarized as The instrumentation needed for NEIGE follows: consists of special radio components on both · The NEIGE receiver shall track and the NetLanders and a Martian orbiter. Table 6 produce an integrated Doppler measurement in the Science Implementation Section of the UHF and X-band carriers being indicates which radio components are needed transmitted coherently by the NetLanders. for support of all NetLander investigations and The precision of these measurements, when which are needed specifically for NEIGE. made over a 60 second integration time, is a CNES will be responsible for building the line-of-sight velocity of 0.1 mm/s. lander radio system. In this proposal we The NEIGE Receiver request funding for a dual-frequency Doppler The NEIGE Receiver’s primary data receiver on the orbiter that meets the NEIGE products will be the two-way integrated requirements. Doppler measurement of the UHF and X-band As this proposal is being written, there is carriers being transmitted coherently by the uncertainty in the programmatic plan for Mars. NetLanders. Links can be established with no For the NEIGE experiment, it is not yet decided more than one NetLander simultaneously. The whether NASA or CNES (or others) will nominal mission duration after a 6 to 11 month supply the communications orbiter for cruise will be 1 Martian year (97 weeks). The NetLander, and what the detailed orbiter minimum mission (again after cruise) is 45 specifications and design will be. However, to weeks. At the time of this writing, the orbital meet the expected timeline for the development parameters are unknown, so it has been of the communications orbiter, it was necessary assumed that the NetLander orbiter will host to submit a proposal to this Discovery the NEIGE Receiver and its nominal orbit is a opportunity for building the portion of the polar, 600 x 1250 km elliptical orbit. NEIGE instrumentation that would fly on the The NEIGE Receiver (Fig. 25) consists of orbiter. Hence, our proposed implementation an X-band antenna pair and an electronics of the NEIGE experiment on the orbiter can not chassis. The antennas point in opposite contain detailed interface specifications at this directions to provide omni-directional coverage time. Rather, we have designed and costed an (no assumptions are made about spacecraft instrument that could be integrated into any pointing except that it is three-axis-stabilized). orbiter design with low risk. We assume that An electronic switch selects which X-band the orbiter will be specifically designed so that antenna is used. The electronics chassis sufficient mass, power, and volume allocations includes 2 boards. The first contains the X- are available for the addition of the NEIGE band low-noise amplifier, two down-converters instrumentation to the orbiter. (one at UHF to baseband and the other X-band to baseband), and an analog-to-digital converter NEIGE Instrumentation on the Orbiter to sample both the UHF and X-band baseband Instrumental Requirements signals. The second board includes digital The key functional requirements levied by signal processing circuitry, including a high- the NetLander geodesy experiment on the performance microprocessor and special- purpose signal processing field programmable gate arrays (FPGAs) to perform the radiometric tracking, data fitting and time-tagging as well as provide the necessary interface with the spacecraft Flight Computer. NEIGE: Orbiter Interface The NEIGE Receiver shall levy the requirements summarized in the Table 18 on the host spacecraft. It is assumed that the host spacecraft will accept, store, and execute Fig. 25: NEIGE instrument electronic block ground command sequences to turn the NEIGE diagram Receiver on just prior to an expected pass with a NetLander surface asset and automatically

NetLander NEIGE: Mars Geodesy Network 37 Table 18: NEIGE Orbiter Interface Mechanical Mass 7 kg (including antennas) Volume: Elec. Chassis 20 x 15 x 15 cm Volume: X-band Antenna 5 x 5 x 2 cm (patch-type) Coaxial Cable of Gore Type 142 (or equivalent) between each antenna and Electronics Chassis. Electrical Power 12 W Input DC Power 28 v, ±7 v Command and Data Interface Dual asynchronous RS-422; up to 57.6 kbps Command and Data Protocol TBD Thermal Temperature Range at Base Plate near mounting point of Electronics Chassis: -10° to +40° C Temperature Control: ±1° C per 15 minutes (maximum pass time) Instrument Antenna Field of View Unobstructed hemispherical field of view; boresight nadir-pointing turn the NEIGE Receiver off after completion assembled using commercial practices. A of the pass. The host spacecraft shall also store complete Engineering Model of the NEIGE and time tag all data produced by the NGR for Receiver will then be fabricated using JPL subsequent downlink through the DSN. flight assembly processes (as documented in It is assumed that the host spacecraft will the mission assurance section of this proposal) provide two asynchronous RS-422 compatible and this build will also not use flight-qualified command and data interfaces through which parts. Two flight models will be assembled, commands are relayed to the NEIGE Receiver based on the engineering models but using JPL and data are passed to the host spacecraft for flight assembly processes and using electronics storage. It is also assumed that the spacecraft parts selected using a tailored approach. will provide unregulated DC power at 28 volts, Whenever possible, a Class S or flight qualified ±7 volts and a frequency reference. The NEIGE MIL-STD part will be procured. If commercial Receiver will be a single-string instrument. parts are purchased, only ones with lot Key Subcontracts: Both the Engineering Test traceability will be used. These parts will be Model and Flight Models will be assembled subjected to limited up-screening (based on the and tested at and by JPL. The digital electronics particular part in question), but the emphasis and all software will be designed, prototyped, will be placed on thorough burn-in (see details fabricated and tested by JPL. The RF below) in order ensure the piece parts flown electronics and the X-band antennas will be will meet the mission requirements. This procured via subcontract with industry. As part approach is less costly than the traditional flight of previous work carried out under other unit approach, but is appropriate for a science ongoing programs, several potential industry instrument with a two year mission life in the contractors have been identified and the relatively benign environment presented in a estimated cost of this contract is based on low Mars orbit. A similar approach has been quotes provided for other projects’ subsystems used for previous flight units on DS-1, GPS- with very similar requirements. MET, and CHAMP. Mission/Quality Assurance Issues: A Qualification/Acceptance Testing: The prototype of the NEIGE Receiver will be built qualification of this design will be done using early in the program to enable early the Flight Spare, with testing at qualification interface/compatibility testing. This unit will be levels (+6dB over expected). Once qualified, fabricated using commercial parts and the Flight Model (FM) will be subjected to testing using acceptance level parameters Table 19: NEIGE Downlink/Uplink Information (+3dB over expected). Testing will include Downlink Uplink vibration testing (random vibration and sine Links 1/week 1/month Data rate (Kbps) 0.1 TBD sweep), thermal-vacuum cycling (10° C Data volume 240 kB/week 200kB/month beyond expected operating range), thermal Allowable bit error rate 10-5 10-5 soak testing (50 hours at +50° C) and Science data destination JPL JPL operational burn-in (greater than 1500 hours

NetLander NEIGE: Mars Geodesy Network 38 Table 21: NEIGE Mass Breakdown total). 200 hours of continuous failure free Item Count Total Mass operation is required prior to FM delivery. RF Switch, 2-pole 1 0.06 NEIGE Uplink/Downlink Requirements Coax Cable 2 0.22 Requirements are shown in Table 19. The Misc. Mounting 1 0.40 NEIGE Receiver will collect Doppler X-band Patch Antenna 2 0.12 measurements during NetLander over-flights Electronics Chassis 1 2.20 once per week. The over-flights will typically CBE Actual Mass 3.00 Mass Reserve 1 1.00 last 6-10 minutes. The data acquired is just the Optional Low Multipath Doppler shift of the returned frequency which 2 3.00 can be recorded at a rate less than 100 bits per UHF Antenna second. The data acquired from each TOTAL with Reserves 7.00 NetLander will be transmitted to the orbiter negotiation with the carrier spacecraft provider, operations center where the NEIGE Receiver when identified. Doppler performance and the data will be unpacked and sent to JPL. The details of the interface between the NEIGE NEIGE Receiver will have to be triggered to Receiver and the spacecraft NetLander Orbiter collect data from the orbiter computer, which Communications Payload are two key areas will require that data acquisition schedule where technical margins are impossible to information be uplinked to the orbiter regularly. assess at this time. Because the NEIGE Receiver is based largely Doppler performance is driven by strict on digital signal processing controlled by multipath requirements. These requirements software, it may be necessary to uplink new will drive antenna placement and spacecraft processing software to the NEIGE Receiver to pointing requirements (which currently have account for unexpected aspects of the signal been specified assuming a benign multipath processing. This will be at most a few times environment). It is currently not possible to during the mission. The software uplink will assess the margin on the 0.1 mm/s requirement, be transmitted to the orbiter to be passed along as key spacecraft accommodation information to the NEIGE Receiver through the serial is unavailable. To mitigate this risk, an interface. additional 1.5 kg and $100k is being carried in NEIGE Resources and Margins our estimates to provide a lower multipath UHF The estimated mass, power, and volume for antenna than may be provided by the Orbiter the NEIGE Receiver are given in the Table 20; Communications Payload. To minimize any a detailed mass breakdown is given in Table multipath problem, the beam pattern of the 21. The values are based on the measured UHF and the X-band antennas must be kept mass, volume and power for the receiver pointed at the specific NetLander within ±60° developed for the GRACE project. The from their bore-sights (which should be co- additional mass for the X-band antennas and pointed) during each “pass”. low-noise amplifier are based on breadboard NEIGE Receiver integration requires access models developed for other Mars missions. to the payload frequency reference as well as The uncertainty in these estimates is less than the UHF received signal. These interfaces are 20%. The allocations and margins are not yet fairly straightforward in principle. determined because they are dependent on Unfortunately, Payload specifics are unknown future negotiations with the NetLander support at this time. It is felt, however, that there is orbiter. sufficient latitude in accommodation that these Technical Margins and Risk risks are acceptable, but need to be retired early The current best estimates of mass, power, (pre-PDR). and data volume provided in Table 20 include at least a 20% reserve and are subject to further Table 20: NEIGE: Resources Resource Current Best Estimate Mass (kg) 7 (33% reserve) Power (Watts) 12.0 (20% reserve) Data Rate (bytes/s) 7.2 peak(100% reserve) Data Volume (kB/wk) 288 (100% reserve)

NetLander NEIGE: Mars Geodesy Network 39 unfold immediately after landing (Fig. 3). The ATMIS: General Mission Information: JPL-supplied ATMIS sensors are deployed To achieve the ATMIS objectives, each of above the deck on the 1-meter long, 2-segment, the 4 NetLanders has identical atmospheric folding ATMIS/ELF boom supplied by Oxford structure and surface meteorology instruments. University (Fig. 26). The instruments on the These instruments are listed in the Science ATMIS/ ELF boom include FMI’s humidity Implementation Section Table 11, along with sensor and the Atmospheric Electric Field their suppliers and flight heritage. (ELF) sensor, as well as the 3 atmospheric Thermocouples (TC’s) and the wind velocity ATMIS Instrument Characteristics sensor described in Table 11. The humidity Atmospheric Structure: The atmospheric sensor is a Vaisala HUMICAP. This capacitive structure investigation (ASI) uses the 3-axis hygrometer is widely used for terrestrial upper- accelerometers and 3-axis gyros included in atmosphere measurements, and was flight each lander’s Entry, Descent, and Landing qualified for the Mars 96 mission. The ELF System (EDLS). The performance and sensor (supplied by CETP, France) is not part calibration of these instruments will be of the ATMIS package, but complements the monitored throughout the cruise phase. The atmospheric science objectives of the EDLS will be activated several minutes before NetLander mission by measuring the entry into the Martian atmosphere, and will atmospheric electric field, conductivity, and continue to take data until after the lander radio noise due to electrical discharges. The comes to rest on the surface. The resulting ELF sensor is a cylindrical electrode located ~768 kbits of data will be downlinked during between the middle and top TC’s on the the first Sol of surface operations. ATMIS/ELF boom (Fig. 26). Surface Meteorology: After landing, the ATMIS surface meteorological instruments ATMIS: NetLander Interface, will operate throughout each Sol for at least one Martian year. FMI will supply an array of Resources and Margins 6 identical (redundant) capacitive aneroid Boom-Mounted Sensors: To simplify the barometers to monitor the atmospheric integration of JPL’s wind sensors and TC’s on pressure. These barometers are mounted on the the ATMIS/ ELF boom, these sensors will use ATMIS electronics board in the NetLander a common electrical connector integrated into warm electronics box, and are vented to the the isothermal block (IB) at the wind sensor atmosphere through a port. Each barometer is a base. A single, shielded, 16-wire cable will run custom Vaisala micro-machined BAROCAP, down the mast to connect these sensors to the like those used for the Mars 96, Cassini ATMIS electronics in the warm electronics Huygens, and MPL MVACS. The ATMIS box. The 3 atmospheric TC’s (ATM TC’s), the Optical Depth Sensor, supplied by Service wind sensor’s 2 ambient temperature TC’s d’Aéronomie of France, is a multi-spectral sky (WTC’s), and the 20 wind direction TC’s (WD imager that was originally developed and TC’s) will use the IB as their reference qualified for the Russian Mars ’96 mission. It is junction. This small (1 cm diameter, 2.5 cm

mounted in the body of the lander with an

TC unobstructed view of the sky. 2

Each lander also includes instruments

ELF

mounted on 2 small booms. These two booms Wind

TC

1 are stored in a folded configuration during Sensor

launch, cruise, and EDL. Immediately after TC

3

landing, they are deployed by torsion springs, HUMICAP after release by fully redundant, flight- Latch qualified wax pellet actuators (Starsys EH3525). The soil and very-near-surface Fig. 26: ATMIS/ELF boom in folded (stowed) atmospheric temperatures will be measured by configuration, showing the locations of each sensors mounted on the Magnetometer boom. sensor. The two gray cylinders below the This small boom is deployed to the surface wind sensor are wax pellet actuators for from one of the 3 solar array petals, which releasing the mast after landing.

NetLander ATMIS: Mars Meteorological Network 40

a total mass of 49.5-g, with 31% margin TC’s

Wind Direction against a 65-g allocation (Table 22).

WTC

1 Sensor Control Electronics: The control

Hot and readout electronics for all of the ATMIS Wires instruments are located in the warm

electronics box, in the body of each

WTC NetLander. The ATMIS electronics are 2

Multiplexer 16 Channel Thermocouple carried on two 120 x120x18 mm electronics

Isothermal

Ref TC boards. Because ATMIS includes no

Block PRT microprocessor, its sensors are controlled and read out by the NetLander command and data

management system (CDMS), which is also

V I TC TC TC V I I V I V

1 2 3

Common PRT Drive p g c d d s r

g supplied by FMI.

for TC’s

and Readout The control and readout electronics for the Fig. 27: Wiring schematic for ATMIS wind JPL wind sensor and TC’s will occupy a single sensors and TC’s. Signals from the ambient 50 x 70 x 10 mm daughter board on one of the temperature TCs (TC1, TC2, TC3), 2 wind ATMIS boards. This daughter board’s mass sensor ambient temperature TC’s (WTC1, cannot exceed 120 g. High-density electronics WTC2) and the 20 direction TC’s are packaging techniques will be used to meet multiplexed on the isothermal block at base of these requirements. We will integrate the the wind sensor. hundreds of discrete analog components of the wind sensor’s hot wire control circuit into a long) berillia block will include a precision single, custom, analog, application-specific PRT (Rosemount 118MF500A) for measuring integrated circuit (ASIC). This ASIC will then the reference junction temperature. A “zero- be integrated into a multi-chip module (MCM), point” TC is also included in the IB to monitor along with the resistors needed to set the hot the voltage offset in the TC amplifiers. A wire over-temperature, a fully-redundant pair common TC ground will be connected to the of TC amplifier circuits, a MUX, and a 14-bit constantan leads of the zero point TC, 3 ATM analog-to-digital converter (Fig. 14). The TC’s, 2 WTC’s, and 10 of the 20 WD TC’s to current best estimate of the MCM mass is 75 + reduce the number of TC leads that must be 15g, providing a 33% mass reserve (Table 22). transferred down the ATMIS/ELF boom (Fig. ASICs and MCMs have been widely used 27). in JPL’s recent flight projects (Cassini, DS1, To further reduce the wire count, the other MISR, etc.), and the proposed designs are no 16 TC leads are connected to a precision, low- more challenging than those. This approach voltage TC multiplexer (MUX) that is satisfies the stringent NetLander mass and incorporated into the IB. This MUX is volume requirements, and provides other controlled and read out by 7 wires (power, advantages. First, even though ASIC’s and ground, counter, step, reset, data, data ground). MCM’s have high development costs, dozens The 16 wires running down the mast include 7 to hundreds of parts are produced in a run, from the MUX, one common TC ground, and 4 reducing their recurring cost. This is an asset wires each (2 current, 2 voltage sense) from the because JPL must deliver 7 flight-like systems IB PRT and the wind sensor hot wire (Fig. 27). (1 EM, 4 flight models, and 2 spares), and The wire allocation is 24, yielding 8 spares. additional systems are needed for qualification The measured mass of the MVACS-derived testing and life tests. The budget and schedule sensors is 29.5-g, and the cable adds ~20 g, for required to make this many hand-built PC Table 22: ATMIS Resources and Margins Resource Allocation Current Best Estimate Margin Mass: Sensors 65g 49.5 g (MVACS*) 15.5 g (31%) Electronics 120g 75 + 15 g 30 g (33%) Power (peak) 0.600 W 0.477 W (MVACS*) 0.123W (26%) Power (avg continuous) 0.365 W 0.282 W (MVACS*) 0.083W (29%) Data Volume (ATMIS Total) 10 Mb/Sol 4.5 Mb/Sol 5.5 Mb/Sol (120%) * MVACS: measured value based on MPL MVACS flight hardware.

NetLander ATMIS: Mars Meteorological Network 41 boards could easily exceed that needed to Regular sampling throughout each Sol and implement the systems proposed here. Second, throughout the seasonal cycle is needed to the use of ASIC/MCM packaging minimizes achieve the objectives of the ATMIS power consumption, and provides more experiment. This places significant demands resistance to mechanical shocks and thermal on the lander power system, but these demands cycles than conventional surface mount boards. are not unique to the sensors proposed here, or These characteristics are important for Mars to ATMIS, since this operating scenario is also surface applications. Third, wind and required by SEIS, MAG, and ELF. The need temperature sensors will be needed on many for uniform sampling also provides some future Mars landers because these properties advantages. In particular, it reduces the need are poorly understood, and can have profound for complicated commanding. In fact, most of effects on the working environment for systems the primary ATMIS objectives could be and instruments. The proposed reductions in achieved if it only ran the default commands size, volume, mass, and power could therefore that are stored on board before launch. benefit future NASA missions, particularly The ATMIS surface sensors will operate small landers (e.g., Scouts). Finally, this using one of the 3 data acquisition modes packaging approach should minimize concerns described on page 24. In each mode, the about technology transfer, because it is unlikely sampling rate, sampling period, and on-board that our partners could reverse-engineer these data processing approach for each sensor can parts even through destructive testing. be specified by command from the ground. However, these parameters will not usually be ATMIS Power Requirements changed, except to accommodate changes in Conditioned power (+5 v and +15 v) for the available lander resources (e.g., power, data ATMIS will be provided by the NetLander volume). In a typical Sol, ATMIS will use power system. The ATMIS allocation is Mode 1 to collect data for 5 out of every 30 specified in terms of a peak power (600 mW), minutes for 22 hours. This sampling mode will and a diurnally integrated energy usage (5 produce ~3.2 Mbits of data. The fast scan Wh/Sol). The JPL wind and temperature modes (2 and 3) will also be used for ~200 sensors account for ~1/3 this allocation on min/Sol, producing 1.3 Mbits/Sol. The total average (365 mW, 1.66 Wh/Sol). Direct budget for the day would then be 4.5 Mbit/Sol, measurements of the MVACS sensors indicated out of a nominal allocation of 10 Mbit/Sol. a peak power of 477 mW, and average power values near 282 mW, yielding 26 and 29% Integration, Test, and Planetary Protection margins, respectively. Also, the JPL sensors The proposed atmospheric temperature and can meet their baseline science objectives with wind sensors will be assembled, qualified, and a duty cycle as small as 4 hours/Sol, yielding a calibrated at JPL, using methods and lessons 47% energy margin (at average power). learned from MPF ASI/Met and MPL MVACS. All parts will be burned in for at least 200 ATMIS: Lander Attitude Requirements hours before delivery. Other parts will be life The JPL wind sensors and TC’s will work tested, simulating the duration and number of properly as long as the deck is oriented on/off cycles anticipated in the NetLander upwards and the ATMIS/ELF mast deploys. mission. The EM and each flight model will The tilt and azimuth of the mast must be known then be shipped to Oxford University, where to with +9o to determine the wind velocities to they will be integrated with the ELF and within +10%. This information can be humidity sensors on the ATMIS/ELF boom and obtained most accurately by acquiring images flight qualified as a system. It will then be of the sun with the PANCAM. shipped to FMI, where it will be integrated with the ATMIS flight electronics and verified. ATMIS Commands and Data Handling: Finally, each system will then be delivered to All flight software for ATMIS will be CNES for spacecraft integration and test. developed by FMI. The JPL sensor control, There, the sensors and electronics will be baked readout, and calibration software will be based at 105°C for 300 hours to satisfy planetary on simple algorithms provided by JPL. protection requirements. JPL will participate in all phases of this process.

NetLander ATMIS: Mars Meteorological Network 42 MANAGEMENT AND SCHEDULE Sponsoring Organization’s Commitment and Consortium and the commitment of CNES to Objectives the Mars Exploration Program. Instrument A consortium of international agencies will proposals were once again submitted for implement the NetLander mission. It is evaluation by a multi-national science review managed by the Centre National d'Etudes board. This board selected the NetLander Spatiales (CNES) of France, which accords it payload, and rated SEIS and ATMIS (and a the highest priority within its Mars Exploration non-U.S. instrument, PANCAM) as the highest Program. The other major players are priority instruments. Ilmatieteen Laitos (Finnish Meteorological Alignment with Sponsoring Organization’s Institute, FMI), and the Deutschen Zentrum für Development and Mission Plans Luft und Raumfahrt (German Space Agency, The NetLander mission and operations plan DLR). As currently planned, the NetLander has been developed over the past several years Mission will be launched in 2005 on an Ariane with input from Drs. Banerdt, Crisp, and 5, with the CNES Mars Orbiter. Folkner, and reflects the design of the The investigations proposed here have been instruments proposed here. The goals of the selected twice by independent European review NetLander mission, as proposed and selected panels, and are critical for achieving the goals by European peer-review panels, require the of the NetLander mission – characterizing the capabilities of the ATMIS, SEIS, and NEIGE global climate and interior structure of Mars. instruments as outlined in this proposal. The NetLander mission was first proposed to Without U.S. participation, the science return the Mars Express Mission in 1998. When mass from the NetLander mission will be constraints on Mars Express resulted in the significantly reduced. deletion of the NetLanders, the mission was proposed to CNES’s small mission program Management Approach. and was selected for support. The U.S. Responsibility for the overall success of the contributions to ATMIS, NEIGE, and SEIS NetLander Mission rests with the NetLander were included in that proposal. The NetLander Consortium. The Principal Investigator for this mission grew out of that proposal with the proposal, Dr. Bruce Banerdt, is responsible for formation of the multi-national NetLander the overall success and scientific integrity of U.S. contributions to the NetLander mission

NASA Discovery Program Office (NMO)

Science Team (JPL) Principal Investigator EPO Coordinator SEIS Lead: Bruce Banerdt Bruce Banerdt, JPL Jim Tillman, UW Seattle NEIGE Lead: Bill Folkner ATMIS Lead: David Crisp Project Manager JPL

Mission Assurance & Safety JPL

ATMIS Instrument Manager NEIGE Instrument Manager SEIS Instrument Manager

Fig. 28: Organization for U.S. Contributions to NetLander Project provides clear lines of authority and responsibility

NetLander Mars Science Network 43 Table 23:Key team members bring a wealth of experience to the Project Team Member Responsibility/Capability Relevant Experience Responsible for overall success of U.S. Bruce Banerdt, PI contributions to NetLander Mission; will also Magellan, MESUR, lead SEIS SP sensor development and analysis MGS Will lead ATMIS wind and temperature sensor MVACS, David Crisp, co-I development and analysis Mars Pathfinder Will lead NEIGE geodesy experiment dual- Mars Pathfinder, William Folkner, co-I band receiver development and analysis Galileo (to be chosen from a JPL Project Manager Project management (U.S. involvement) qualified pool) Project management, provide orbiter and NetLander Consortium landers, mission ops and is the final project authority on all issues the lowest level possible while ensuring that a related to those contributions. To perform that decision made in one system does not adversely responsibility successfully, the PI has affect another or the science data return. The PI established the NetLander project as an is the final project authority for all decisions integrated partnership. In addition to his PI that cannot be resolved at lower levels and in role, Dr. Banerdt will lead the development and particular for any involving the quality and data analysis efforts for the SEIS instrument. quantity of science data deliverables. Dr. William Folkner will lead the NEIGE Teaming Arrangements effort, while Dr. David Crisp will lead the Teaming arrangements will be formalized effort for ATMIS. Each was named as a co-PI with a Memorandum of Understanding between in the European NetLander proposal, and will NASA and CNES. JPL will manage U.S. team with an Instrument Manager chosen for contributions to the project under a task order their experience in the design and development executed as part of JPL’s existing NASA of the proposed instruments. These contract. An International Agency MoU with Effective management processes and CNES will be executed upon NASA’s decision institutionally supported tools will be available to proceed. MoU’s with other NetLander to assist the NetLander Project. Critical issues Consortium Partners (e.g., FMI) will also be and reviews will be accomplished in face-to- executed at that time if necessary. face meetings. A web-based ISO 9001 compliant electronic library will provide easy Roles and Responsibilities of the Principal access to project documents and quality records Investigator and Project Manager while maintaining security and configuration Dr. Banerdt is in charge of the investigation control. and maintains full authority for its scientific integrity and for the integrity of all other Organization and Decision-Making Process aspects of the mission, including E/PO. He The management organization for the U.S. delegates the responsibility for implementation contributions to NetLander is shown in Fig. 28, of the flight system to the JPL Project Manager and described in greater detail in Table 23. The (PM). Upon selection, JPL will appoint a PM PI is responsible to NASA Headquarters for the with Dr. Banerdt’s concurrence. The PM will successful execution of the U.S. contributions be chosen from a pool of candidates who are to the mission. He is prepared to recommend qualified by virtue of past flight system termination of the project in the unlikely event development management experience and that achievement of the science goals should training in modern management techniques. become impossible within project resources. The PM will plan, coordinate, and monitor The PI assigns project management system design and implementation during all responsibility to the JPL Project Manager. The phases of the project. The PM will also be Science Team is under the leadership of the PI responsible for coordinating the international but all financial reporting is through the Project agreements necessary for the international Manager. All instrument managers report to the cooperation and the export of the hardware, as Project Manager. Decision making will occur at outlined in Appendix 4. A Project Plan will be

NetLander Mars Science Network 44 developed that will include specific spending assessment and management approach is the plans and development milestones that will be use of informal peer reviews at the sub-system used as the basis of an earned value level for all JPL deliverables. This proposal performance measurement tracking system. includes an estimate of the cost associated with The Project Plan will also document the initial risk management based on analogy with similar level of project reserves and a schedule for missions under development at JPL. For their depletion tied to key project milestones. further details, see the Mission Assurance The PI will have approval authority over the section in the Mission Implementation Section. Project Plan and all other project level Management Strategy for Release of documents, as well as any changes to those Technical, Cost, Schedule, and Science documents. The PI will report to NASA all Reserves changes to the plan and descope options The mission architecture contains technical, exercised, if any, for NASA concurrence. The cost, and schedule reserves that are considered PM will report monthly against the Project Plan adequate to cover design and development and periodically review the completion plan to uncertainties. After selection, a margin assure that it is proceeding within schedule and management and reserve depletion plan will be cost. The PM will report progress and any developed. It will specify the project’s problems to the PI in weekly meetings or commitment to maintaining a certain level of teleconferences. Monthly reports to the key reserves at development milestones, Discovery Program Office at the NASA especially PDR, CDR and beginning of system Management Office (NMO) will be prepared test. The project is prepared to exercise de- by the PM and approved by the PI. scope options in order to maintain an Roles and Responsibilities of Mission appropriate level of reserves throughout the Assurance Manager development cycle. The PM will control the The Mission Assurance Manager is the key expenditure of reserves except where quality or individual for coordination of Mission quantity of science data is affected. In those Assurance and Safety activities of all partners. cases the PI will exercise final authority. Risk Management and Risk Mitigation Plan Reviews and Reporting The key element in managing project risk is A cost-effective and formal review program the establishment and management of will contain reviews of heritage hardware appropriate project reserves, and the and/or design pedigrees to determine the establishment of a Project Plan against which applicability of design, test, and flight history progress will be tracked, in order to determine relative to the mission requirements. Formal as early as possible when project reserves will reviews such as PDR, CDR, pre-ship, etc., will be needed. The NetLander risk management be supplemented with a series of peer reviews plan will be compliant with NPG 7120.5a. that provide an in-depth analysis of each The basis of estimate for our cost reserves hardware and software element. Peer reviews is described in the Cost Methodology section of will be a continuous process throughout the this proposal. Due to the nature of the NetLander instrument development phase. A international cooperation, and uncertainties in summary of peer reviews will be included in interfaces, generous cost reserves have been the formal design reviews. allocated for the NetLander project instrument Project Schedule development. Funded schedule reserve for each A project schedule showing all mission instrument is explicitly shown on the schedules phases and major milestones is shown on the on the following pages. following pages. After selection, the Modern risk management tools such as instruments’ system requirements and designs failure modes and effects analysis, fault tree will be finalized. The architecture will include analysis, probabilistic risk assessments, parts a firm cost limit, detailed descope plan, and the stress analysis, worst case analysis, hazard PI’s decision criteria for any deviations from analysis, etc., will be employed as they have the baseline mission. There are 30 days of fully been on recent JPL-managed low-cost funded schedule reserve on the critical path just missions. Another key element in our risk before delivery to flight system integration,

NetLander Mars Science Network 45 providing one month of fully funded schedule assumed to require less than 1 month. Given reserve per year of pre-launch flight system this assumption, and the one month of schedule development. margin per calendar year, there is sufficient ATMIS Delivery margin in the overall schedule to account for Before delivery to CNES for system the current uncertainty on the spacecraft integration, the ATMIS wind and temperature contractor and still make FM delivery on sensors must be integrated onto the ATMIS/ 02/01/04. ELF boom at Oxford University, and the SEIS Delivery electronics must be integrated into the flight There will be two deliveries of SEIS SP to board at FMI. These two tasks should require the French SEIS team at IPGP for integration. less than one month per delivery and can be The first delivery will be two EM’s for initial carried out in parallel at Oxford and FMI. The system testing on 11/21/2001. The second mast and electronics subsystems must then be delivery will be comprised of all four flight integrated and tested at FMI before shipment to models and the two flight spares on 2/17/2003. CNES. This step should also require less than The FM/Spare deliveries are simultaneous 1 month per delivery. rather than phased due to the batch fabrication While it is possible to deliver flight-like of the microseismometers. The indicated EM sensors to Oxford by 11/13/01, the flight- Preliminary and Critical Design Reviews will like EM electronics will not be ready before allow for timely oversight and will involve both 2/1/02. To mitigate any schedule delays this JPL and our IPGP collaborators. might cause, JPL will deliver a functioning Overall the schedule has been phased to electronics brassboard to FMI on or before minimize the peak number of personnel 11/13/01. This brassboard will be interfaced to required by maintaining continuous work for the ATMIS board by a connector that simulates the team throughout the design, fabrication, the form of the wind/temperature daughter testing and integration. By so focussing the board. When the flight-like daughter board is work, the outlined aggressive schedule will be ready, the connector will be unsoldered and met within the budget. replaced by this unit. The target for completing the first flight model (FM1) is 10/4/02. Because it would be most efficient to batch fabricate, qualify, and calibrate Flight Models 2 - 4 and the Flight spares, JPL plans deliver these systems to Oxford and FMI by 28 May 2003. We will then to spend the remainder of FY 03 and 04 supporting the sub-system integration and qualification tests at CNES. The team will then staff down, keeping only a skeleton crew to support and document the final system-level tests at CNES. NEIGE Delivery The target for completing the flight model (FM) is not a particularly difficult schedule to meet. The key challenge will be to develop the EM by 02/01/03 in order to facilitate early interface testing with the spacecraft contractor. This will therefore put pressure on the planned prototype development schedule which calls for prototype completion by 12/01/01. Before delivery of the FM to the orbiter contractor for system integration, the completed NEIGE Instrument will be undergo full acceptance testing and burn-in here at JPL. This testing is

NetLander Mars Science Network 46 Start Finish 2001 2002 2003 2004 2005 2006 2007 2008 Activity Name Date Date 1 2 3 4 1 2 3 4 1 2 3 4 1 2 3 4 1 2 3 4 1 2 3 4 1 2 3 4 1 2 3 4 Mission PDR 6/12/01 Mission CDR 6/11/02 Launch 8/10/05 Arrival at Mars 8/26/06 End of Mission 9/1/08

SEIS EQM delivery due 11/22/01 completion --> req. date 10/25/01 11/22/01 FM1 delivery due 2/18/03 completion --> req. date 1/14/03 2/18/03 FM2 delivery due 9/2/03 completion --> req. date 1/14/03 9/2/03 FM3 delivery due 1/20/04 completion --> req. date 1/14/03 1/20/04 FM4 delivery due 5/11/04 completion --> req. date 1/14/03 5/11/04

NEIGE EQM delivery due 4/1/03 completion --> req. date 11/1/02 4/1/03 FM delivery due 2/2/04 completion --> req. date 11/27/03 2/2/04

ATMIS EQM sensor due 11/19/01 completion --> req. date 10/12/01 11/19/01 EQM electronics due 1/21/02 completion --> req. date 1/4/02 1/21/02 FM1 sensor due 11/4/02 completion --> req. date 9/23/02 11/4/02 FM1 electronics due 1/4/03 completion --> req. date 9/23/02 1/4/03 FM2 sensor due 7/2/03 completion --> req. date 5/20/03 7/2/03 FM2 electronics due 8/2/03 completion --> req. date 5/20/03 8/2/03 FM3 sensor due 10/20/03 completion --> req. date 5/20/03 10/20/03 FM3 electronics due 11/20/03 completion --> req. date 5/20/03 11/20/03 FM4 sensor due 3/11/04 completion --> req. date 5/20/03 3/11/04 FM4 electronics due 4/11/04 completion --> req. date 5/20/03 4/11/04 1 2 3 4 1 2 3 4 1 2 3 4 1 2 3 4 1 2 3 4 1 2 3 4 1 2 3 4 1 2 3 4 NetLander Milestones: deadlines for U.S. contributions shown by red circles; time between ATMIS Schedule: plan to meet NetLander milestones anticipated completion of component and required deliveries in black. Funded reserve shown on following instrument-specific schedules.

NetLander Mars Science Network 47 NEIGE Schedule: plan to meet NetLander milestones SEIS Schedule: plan to meet NetLander milestones

NetLander Mars Science Network 48 COST AND COST ESTIMATING METHODOLOGY Cost Estimating Methodology surface operations phase. The estimates include All instrument costs in this proposal were travel to science team meetings, instrument provided by Instrument Managers based on sub-system and system-level calibration instrument heritage, and have been approved by exercises, operational readiness tests, and management of the JPL Divisions responsible science conferences and workshops to present for instrument development, assembly, and test. NetLander plans and products. Estimates also Science workforce estimates were provided by include publication expenses and computer the Science team members based on previous support services. experience. All labor rates were calculated Instrument Development Cost Details assuming a majority of JPL Senior or Principal ATMIS: The workforce estimates for the level personnel, commensurate with the NetLander ATMIS team members were based experience of the Instrument and Science on our current understanding of the NetLander Teams. JPL burden rates were generated with mission requirements, and our experience with the Proposal Costing and Analysis Tool past Mars missions. This experience includes (PCAT), a JPL in-house developed Grass Roots the Mars Pathfinder Lander Atmospheric Cost estimation tool that strictly follows JPL's Structure Investigation/Meteorology (ASI/Met) published accounting practices. It uses experiment, and the Mars Polar Lander/Mars aggregate "Bid" salaries where appropriate and Volatile and Climate Surveyor Meteorology applies all JPL required Allocated Direct Costs (MPL MVACS Met) experiment. The (ADC's) and Fees. It generates all required proposed budget includes support for sensor tables B2 and B3 (pages 52-53), in the format and electronics design, fabrication, specified by the AO. qualification, calibration, documentation, and Reserve Strategy reviews at JPL. It also includes the funding 30% reserve is carried on all instrument needed for full participation in the delivery, and costs, above 1 month funded schedule the sub-system and system-level integration reserve/year of effort. While this may seem and test activities at Oxford, FMI, and CNES. conservative given the heritage of the NEIGE: The costing of the NEIGE flight instruments, this reserve is held to cover instrument was developed using costing-by- schedule slips by our European partners, as analogy based on recent past experience; well as any interface changes which may occur specifically the GRACE mission (nearing during the mission planning phase. In addition, Flight Model Delivery) and the Mars Network a 20% reserve on Management and Science Transceiver for 2003 (currently in Phase A costs will also be maintained, to cover Formulation). Instrument heritage includes unanticipated support requirements or travel. commercially available, flight proven RF Science Cost Details hardware components (including Antennas, For each instrument, implementation phase Upconverters, Downconverters, and Power workforce estimates include funding needed for Amplifiers). The digital processor hardware, science involvement in: instrument design team which is designed to perform the Doppler meetings; development of formal science measurements, is largely inherited from the requirements; input to functional requirements primary GRACE instrument (2001 launch). and interface requirement documents; The GRACE instrument was designed and development of characterization and calibration tested to make Doppler measurements with an plans; development, implementation, and order of magnitude greater precision. In validation of algorithms for converting raw addition, the Autonomous Formation Flyer data to calibrated values and higher level Instrument for the New Millennium Program’s products; and participation in formal reviews. Space Technology 3 mission has multipath During the Operations phase, science funding is suppression requirements very similar to included to support full participation in the NEIGE. The ST-3 mission has roughly the participation in operational readiness tests prior same schedule of deliveries as NEIGE. The to landing, and planning, command generation, techniques employed by GRACE and ST-3 will data acquisition, and data analysis during be adapted to the NEIGE instrument to achieve the required high level of performance.

NetLander Mars Science Network 49 SEIS: Costing for the microseismometer was includes support for selecting optimal tracking performed with reference to two other flight passes and working with the Deep Space instruments of similar complexity, a Network to obtain the required orbiter tracking microgyroscope for X-33 and an atomic force data. microscope for the Mars ’01 MECA payload. NEIGE requires high-precision Doppler Both of these instruments consist of a measurements of the orbiter within the 24-hour micromachined silicon array with transducer period in which the dual-band Doppler and control electronics. Batch micromachining measurements are made between the orbiter techniques allow for considerable efficiency in and the NetLanders. The Doppler providing the 12 flight sensors required. All measurement accuracy requirement is 0.1mm/s flight units will be delivered simultaneously, for 60s integration times, which is typical of X- minimizing workforce beyond 2003. band data acquired by the DSN. To acquire this Mission Operations Support: NetLander tracking data, a budget is included for 8 hours SEIS and ATMIS Operations are expected to per week of DSN tracking at a 34m antenna be relatively simple and repetitive after an during the 98 weeks (one Martian year) of the initial break-in period. Immediately after prime science mission. The only data required landing, we anticipate that the US members of from the DSN from these tracking passes is the the ATMIS and SEIS teams will work at the Doppler measurement. It is also possible to CNES Operations Center for up to one month receive telemetry from the orbiter during this so that we can contribute to the around-the- time. However the handling of telemetry data clock acquisition, interpretation, and falls within the responsibilities of the commanding activities. Once these tasks supporting orbiter and hence is outside the become more routine, we will return to our scope of this proposal. home institutions and conduct operations remotely for up to one Martian year (~26 Table 24 below shows the workforce months). To support remote operations, we allocations for each year (work years/FY) of must set up and maintain a secure command effort as a function of an abbreviated and data interface between JPL and the NetLander WBS (the portion relevant to the NetLander Operations Center at CNES. Our instrument builds), while Table 25 shows a full recent experience on MPF, MGS, and MPL costed WBS Basis-of-Estimate. indicates that these functions can be carried out by science team members Table 24: Abbreviated WBS: Engineering Workforce for with assistance from a part-time Instrument Builds WBS Element FY01 FY02 FY03 FY04 FY05 FY0 FY07 FY08 computer system administrator with 1.0 Proj Office. 1.1 Proj. Management 0.7 1.0 1.0 1.0 0.5 0.2 0.2 0.2 flight operations experience. Support for 1.2 Proj. Supp. 0.7 1.0 1.0 1.0 0.5 0.2 0.2 0.2 this function is included in the ATMIS 1.6 Mission Assurance Manager 0.2 0.2 0.1 0.1 2.0 Instruments and SEIS Operations Phase budgets. 2.3 ATMIS NEIGE data consists of Doppler data 2.3.1 Inst. Management 0.4 0.4 0.3 0.2 0.1 2.3.2 Electrical 1.24 1.30 0.14 taken between a lander and an orbiter 2.3.3 Mech/Therm 1.39 1.27 0.23 2.3.4 Software 0.21 0.60 0.30 and between the orbiter and the Earth. 2.3.5 Elec. Ground Supp. 0.28 0.68 0.34 The science team has much experience in 2.3.6 I&T 0.08 1.13 1.11 2.3.7 S/C Int. 0.40 0.30 0.20 data analysis between an orbiter and the 2.3.8 Systems Engineering 0.3 0.6 0.3 0.1 0.1 Earth, and between Earth tracking 2.3.9 Safety/Mission Assurance 0.1 0.2 0.2 0.2 2.4 NEIGE stations and Earth orbiters. The data 2.4.1 Inst. Management. 0.82 1.10 1.10 0.96 0.69 2.4.2 Electrical 1.25 4.33 3.89 2.46 taken between the NetLanders and the 2.4.3 Mech/Therm 0.14 0.62 0.13 orbiter will be a new tracking data type 2.4.4 Software 1.93 4.64 2.65 1.16 2.4.5 Elec. Ground Supp. 0.57 that will require modifications to the data 2.4.6 I&T 0.30 0.34 0.34 analysis programs. The NEIGE Science 2.4.7 S/C Int. 0.45 0.57 2.4.8 Systems Engineering 0.5 0.4 and Data analysis budget includes the 2.4.9 Safety/Mission Assurance 0.05 0.75 0.75 0.35 2.5 SEIS necessary software modification, with 2.5.1 Inst. Management 0.25 0.4 0.4 0.2 0.2 level of effort based on previous 2.5.2 Electrical 0.37 0.50 2.5.3 Mech/Therm 0.52 0.70 0.20 experience in adapting data analysis 2.5.4 Software 0.07 0.10 software for new data types. The 2.5.5 Elec. Ground Supp. 0.07 0.10 2.5.6 I&T 0.72 0.62 0.20 Science and Data analysis budget also 2.5.7 S/C Int. 2.5.8 Systems Engineering 0.04 0.06 0.06 2.5.9 Safety/Mission Assurance 0.05 0.75 0.75 0.35 NetLander Mars Science Network 50 Table 25: NetLander Costed WBS WBS Element FY01 FY02 FY03 FY04 FY05 FY06 FY07 FY08 Total (RY$) 1.0 Proj Office. 2066 2528 1793 1274 665 643 683 526 10177 1.1 Proj. Man. 169 232 244 256 134 56 60 62 1212 1.2 Proj. Supp. 80 110 115 119 61 25 27 27 564 1.3 Travel 3 4 5 5 5 5 5 5 37 1.4 Services 3 4 5 5 5 5 5 5 37 1.5 OAO/DNS 6 8 8 9 9 9 9 10 69 1.6 Mission Assurance 37 38 20 21 117 1.7 E/PO 512 14 27 15 29 41 21 17 676 1.8 Reserves 1255 2118 1370 845 422 501 555 399 7464 1.8.1 Science/Management(20%) 129 187 204 230 302 501 555 399 2507 1.8.2 Instruments (30%) 1125 1931 1165 615 120 4957 2.0 Instruments 3750 6437 3884 2051 399 16522 2.1 Inst. Man. Instrument Management, Systems Engineering, and Quality Assurance costed at the Instrument level 2.2 Inst. Sys E. 2.3 ATMIS 1397 1907 679 472 136 4591 2.3.1 Inst. Man 675 783 51 310 51 1870 2.3.2 Electrical 226 247 27 500 2.3.3 Mech/Therm 247 234 48 528 2.3.4 Software 34 100 52 186 2.3.5 Elec. Ground Supp. 46 118 62 226 2.3.6 I&T 15 196 203 413 2.3.7 S/C Int. 72 67 44 183 2.3.8 Systems Engineering 139 191 125 53 41 549 2.3.9 Safety/Mission Assurance 14 38 40 42 134 2.4 NEIGE 1731 3668 2828 1434 193 9854 2.4.1 Inst. Man. 584 259 281 279 193 1596 2.4.2 Electrical 621 1812 1563 536 4532 2.4.3 Mech/Therm 25 130 51 206 2.4.4 Software 346 851 525 229 1951 2.4.5 Elec. Ground Supp. 218 218 2.4.6 I&T 58 182 251 491 2.4.7 S/C Int. 76 103 179 2.4.8 Systems Engineering 92 81 172 2.4.9 Safety/Mission Assurance 63 258 151 36 508 2.5 SEIS 623 863 376 145 70 2077 2.5.1 Inst. Man 256 310 131 71 70 838 2.5.2 Electrical 69 95 165 2.5.3 Mech/Therm 116 143 40 299 2.5.4 Software 14 19 33 2.5.5 Elec. Ground Supp. 14 19 33 2.5.6 I&T 135 119 40 293 2.5.7 S/C Int. 2.5.8 Systems Engineering 10 14 15 38 2.5.9 Safety/Mission Assurance 9 143 151 74 377 3.0 S/C Bus 4.0 S/C AIT All Spacecraft Operations responsibility of NetLander Consortium 5.0 Launch Check & Orbital Ops. 6.0 Science Support 357 536 626 734 1296 2197 2242 1714 9701 6.1 ATMIS 176 243 231 251 463 904 944 676 3887 6.1.1 Science Management 87 119 94 66 69 181 232 239 1086 6.1.2 Algorithm Dev. & Val. 6.1.3 Mission Ops 115 123 127 365 6.1.4 Data Analysis 97 104 106 307 6.1.5. Reporting/Reviews 6.1.6. Co-investigators 83 117 130 177 386 502 476 195 2064 6.1.7 DSN/Telephone 4 5 6 6 6 6 6 7 46 6.1.8. Travel 2 2 2 2 2 3 3 3 19 6.2 NEIGE 104 189 285 332 479 615 617 436 3057 6.2.1 Science Management 42 58 61 64 134 140 150 77 724 6.2.2 Algorithm Dev. & Val. 33 69 71 73 39 284 6.2.3 Instrument Support 6 6 8 8 7 6 6 3 51 6.2.4 Data Analysis 10 13 14 14 15 15 15 16 112 6.2.5 Reporting and Reviews 4 5 6 6 6 6 6 7 46 6.2.6 Ops. Center Dev. 115 123 127 365 6.2.7 Co-I 1 42 58 61 64 134 140 150 77 724 6.2.8 Co-I 2 49 103 108 113 119 127 130 750 6.3 SEIS 77 104 109 151 354 678 681 602 2757 6.3.1. Science Mgmt. 43 60 63 66 138 217 232 239 1057 6.3.2 Sci. Support 31 42 44 46 48 101 108 111 532 6.3.3. Ops. Engr. 46 194 207 159 607 6.3.4. Data Analysis 38 80 85 87 291 6.3.5. Programmer 37 77 80 43 236 6.3.6. Travel 3 2 2 2 6 6 6 5 34 7.0 Pre-Launch GDS/MOS Dev. Included in Science Support Section 8.0 Mission Ops and DA 9.0 DSN or other tracking 208 427 170 805 9.1 ATMIS 9.2 NEIGE 208 427 170 805 9.3 SEIS TOTAL 37206

NetLander Mars Science Network 51 Table B2: NASA OSS COST FUNDING PROFILE TEMPLATE FOR MISSIONS OF OPPORTUNITY FY costs in Fixed Year FY01 Dollars (to nearest thousand) Totals Cost Elements** FY01 FY02 FY03 FY04 FY05 FY06 FY07 FY08 FY01$ RY$ Phase B (Definition) Management and E/PO 810 ------$810 $810 ATMIS 1,572 ------$1,572 $1,572 NEIGE 1,835 ------$1,835 $1,835 SEIS 700 ------$700 $700 Reserves 1,256 ------$1,256 $1,256 Total Phase B 6,173 ------$6,173 $6,173 Phase C/D (Design/Development) Proj. Mgmt/Miss. Analysis. - 385 373 378 189 - - - $1,325 $1,421 E/PO - 13 25 14 26 - - - $78 $85 ATMIS Systems Eng. - 982 204 370 81 - - - $1,637 $1,726 ATMIS Inst. Int., Assembly and Test - 753 377 61 39 - - - $1,230 $1,288 NEIGE Systems Eng. - 390 406 287 171 - - - $1,254 $1,342 NEIGE Inst. Int., Assembly and Test - 2,956 2,255 1,021 - - - - $6,232 $6,564 SEIS Systems Eng. - 722 316 132 62 - - - $1,232 $1,295 SEIS Inst. Int., Assembly and Test - 115 38 - - - - - $153 $159 Subtotal - Instruments - 5,918 3,596 1,872 354 - - - $11,739 $12,374 ATMIS Science Team Support - 236 218 229 410 - - - $1,092 $1,189 ATMIS Pre-launch MOS/GDS Dev. - 115 58 - - - - - $173 $180 ATMIS Facilities and Administration ------$- $- NEIGE Science Team Support - 183 268 303 424 - - - $1,179 $1,285 NEIGE Pre-launch MOS/GDS Dev. - 211 ------$211 $218 NEIGE Facilities and Administration ------$- $- SEIS Science Team Support - 101 103 138 313 - - - $654 $718 SEIS Pre-launch MOS/GDS Dev. ------$- $- SEIS Facilities and Administration ------$- $- Subtotal Phase C/D before Reserves - 7,161 4,641 2,933 1,716 - - - $16,450 $17,469 Instrument Reserves - 1,873 1,096 562 106 - - - $3,637 $3,832 Other Reserves - 181 192 209 267 - - - $850 $922 Total Phase C/D - 9,215 5,929 3,704 2,089 - - - $20,937 $22,223 Phase E (Operations) Project Management - - - - - 87 89 88 $264 $317 E/PO - - - - - 36 17 14 $67 $80 ATMIS Mission Operations - - - - - 99 103 102 $304 $365 ATMIS Data Analysis - - - - - 677 683 443 $1,803 $2,158 ATMIS DSN/Tracking ------$- $- ATMIS Facilities and Administration ------$- $- NEIGE Mission Operations - - - - - 99 103 102 $304 $365 NEIGE Data Analysis - - - - - 429 411 250 $1,090 $1,303 NEIGE DSN/Tracking - - - - - 178 355 138 $671 $805 NEIGE Facilities and Administration ------$- $- SEIS Mission Operations - - - - - 167 172 129 $468 $561 SEIS Data Analysis - - - - - 416 395 357 $1,168 $1,401 SEIS DSN/Tracking ------$- $- SEIS Facilities and Administration ------$- $- Subtotal Phase E before Reserves - - - - - 2,186 2,329 1,624 $6,139 $7,355 Reserves - - - - - 430 462 322 $1,214 $1,455 Total Phase E - - - - - 2,617 2,791 1,946 $7,354 $8,810 Launch Services - $- $- Total NASA Cost 6,173 9,215 5,929 3,704 2,089 2,617 2,791 1,946 $34,463 $37,206 Contributions ------$- $- Total Contributions ------$- $- Total Mission Cost = $34,463 $37,206

NetLander Mars Science Network 52 Table B3: MISSION PHASE SUMMARY OF NASA OSS COST FY costs in Real Year Dollars (to nearest thousand) TOTALS Mission Phase FY01 FY02 FY03 FY04 FY05 FY06 FY07 FY08 FY09 RY$ FY01$ Management and E/PO Phase B 2,066 ------$2,066 $2,066 Management and E/PO Phase C/D - 2,528 1,793 1,274 665 - - - - $6,259 $5,889 Management and E/PO Phase E - - - - - 643 683 526 - $1,852 $1,545 ATMIS Phase B 1,572 ------$1,572 $1,572 ATMIS Phase C/D - 2,150 911 723 599 - - - - $4,383 $4,132 ATMIS Phase E - - - - - 904 944 676 - $2,523 $2,107 NEIGE Phase B 1,835 ------$1,835 $1,835 NEIGE Phase C/D - 3,856 3,114 1,767 673 - - - - $9,409 $8,877 NEIGE Phase E - - - - - 823 1,044 607 - $2,473 $2,065 SEIS Phase B 700 ------$700 $700 SEIS Phase C/D - 967 485 296 423 - - - - $2,172 $2,039 SEIS Phase E - - - - - 678 681 602 - $1,962 $1,636 Launch Services $- $- Total OSS Discovery Mission Cost 6,173 9,501 6,302 4,059 2,360 3,048 3,352 2,410 - $37,206 $34,463 Extended Mission $- $- Participating Scientist Program 1,500 1,500 1,500 $4,500 $3,748 Data Analysis Program 1,000 1,000 1,000 $3,000 $2,424 Total NASA Cost 6,173 9,501 6,302 4,059 2,360 4,548 5,852 4,910 1,000 $44,706 $40,636 Total Contributions Total Mission Cost = $37,206 $34,463 JPL Cost Accumulation System The NASA prime contract—NAS7-1260, or its successor contract—is a Cost Reimbursable Award Fee type instrument. All costs incurred are billed to the Government on a 100% reimbursable basis. The costs to be charged for the proposed work must be consistent with contractual provisions and established procedures for costing under the current contract between NASA and Caltech. All charges developed at the Laboratory, including JPL applied burdens, are paid by the Government via draws against a Letter of Credit as direct charges at the rates in effect at the time the work is accomplished. Government audit is performed on a continuing basis by a Defense Contract Audit Agency team in residence. Allocated Direct Costs (ADC) is the term for “JPL applied burdens.” ADC includes activities (accounts) benefiting multiple tasks. The cost collection system groups common Allocated Direct Cost accounts into three groups. The groups are as follows: 1. Labor: Labor ADC 2. Procurement: Purchase Order ADC and Subcontract ADC. 3. General: a percentage of all subordinate costs on direct projects. (Similar to the General and Administrative expense in industry.) Each grouping contains like functions or activities. The accounting process distributes these costs on a 100% reimbursable basis. Multiple Program Support (MPS) is a distributed direct factor per JPL and accountable contractor workhour on respective program office direct accounts. Labor—Employee Benefits consist of three labor fringe rates applied to direct labor as follows: Paid Leave is a percentage of straight time labor costs; Vacation is a percentage of straight time labor cost and Paid Leave costs; Benefits is a percentage of straight time and overtime labor costs, Paid Leave costs, and Vacation costs. Performance Incentive Award - the NASA/Caltech contract for the operation of the federally funded research and development center (FFRDC) is a cost plus award fee contract. As such, all sponsors placing funds on contract contribute a small percentage (0.9%) of task order dollars toward the award fee. Facilities and Administrative (F&A) Costs - Virtually all work performed at JPL is for a single final cost objective—the NASA Prime Contract (NAS-1407). All JPL costs are direct. There are no indirect cost categories at JPL. JPL recovers performance fees and a negotiated lump sum in-lieu-of indirect costs as a direct cost. JPL has no negotiated pricing or charging rates and seeks reimbursements from the government based on raw direct as well as allocated direct cost rates. JPL’s accounting system does not serve as the basis for receiving reimbursements under the contract. The accounting system—including job costing, accruals, inventory valuations and apportioned costs—is used for NASA budget and reporting purposes. JPL does not bill the government for costs. For work performed under the Contract, NASA provides JPL the authority to incur costs, and for The California Institute of Technology to receive reimbursements via a draw from a Letter of Credit.

Cognizant Federal Agency: NASA Management Office – Jet Propulsion Laboratory M/S 180-801 Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive Pasadena, CA 91109-8099

NetLander Mars Science Network 53 APPENDIX 1: Statement of Work

THE NETLANDER PROJECT JPL Draft Task Plan to the National Aeronautics and Space Administration August 1, 2000

JET PROPULSION LABORATORY California Institute of Technology Pasadena, California 91109

1. INTRODUCTION U.S. participation in the NetLander Mission, including science objectives, requirements, and schedule, is described in the NetLander Discovery Mission of Opportunity Proposal, dated August 1, 2000. This task plan describes the Project to be performed by the Jet Propulsion Laboratory (JPL) and the U.S. portion of the NetLander Team. Note that NASA and CNES are currently drafting an Memorandum of Understanding which describes the responsibilities of all parties in the NetLander collaboration, and that the responsibilities outlined in that document will supercede those described here, should discrepancies between the two documents occur. 2. SCOPE OF WORK JPL will contribute hardware and analysis support for three experiments on the NetLander Project: ATMIS, SEIS, and NEIGE. These experiments are part of an international collaboration to send four landers to Mars, and will be integrated into the spacecraft and launched by the Centre National d’Etudes Spatiales (CNES). JPL's work includes: a. Assisting the international NetLander Team in (1) assessing the mission's feasibility, (2) developing programmatic constraints and trade-off criteria, and (3) establishing a Science Team to refine the Science Requirements, Mission Design, and Science Analysis Plan, b. Specific to ATMIS (ATmospheric Meteorological Instrumentation System): design, build, and test a wind sensor and temperature sensors for operation in the Martian environment, deliver the products to Oxford University for integration onto the ATMIS/ELF boom, provide integration and test support, and science analysis and operations support after launch, c. Specific to NEIGE (NetLander Ionosphere and Geodesy Experiment): design, build, and test a dual-band Doppler receiver for operation in the Martian orbital environment, deliver the product to CNES for integration onto the orbiter, provide integration and test support, and science analysis and operations support after launch, d. Specific to SEIS (NetLander SEISmometer): design, build, and test short-period seismometers for operation in the Martian environment (four such systems will be built), deliver the seismometer systems to CNES for integration onto the landers, provide integration and test support, and science analysis and operations support after launch, e. Providing day-to-day management and coordination of the U.S. portion of the Project as delegated by the PI, including monitoring and reporting technical progress and financial status, and performing a Preliminary Design and Phase C/D/E Review, a Critical Design Review, and a Pre-ship Readiness Review. 3. DELIVERABLES JPL will deliver or perform the above work as described in the NetLander Proposal schedules attached to this document. 4. GOVERNMENT RESPONSIBILITIES An MoU between NASA and CNES is under development. It outlines U.S. responsibilities in a cooperative effort which encompasses the NetLander Project. 5. PERIOD OF PERFORMANCE The period of performance will be from January 1, 2001 through 31 December 2008. 6. COST ESTIMATE The estimated cost for JPL to perform the NetLander Project as described above is shown on the attached table which is taken from the Discovery NetLander Proposal. The estimated cost includes costs for use, if needed, of the government facilities and services listed below: 1.Environmental testing facilities (JPL) The estimated cost excludes costs for (1) any services or equipment provided as part of the NASA/CNES MoU and (2) the costs of the Participating Scientist Program (PSP).

NetLander Mars Science Network 54 APPENDIX 2: Letters of Endorsement

Paris, July 27, 2000 Ref DPI/E2U- 200/161

Direction des Programmes Dr William Folkner et de la Politique Industrielle Dr Dave Crisp Délégation à l'étude et l'exploration de l'Univers Dr Bruce Banerdt JPL 4800 Oak Grove Dr. Pasadena CA 91109 Dear Colleagues,

The NEIGE, SEIS, ATMIS experiments onboard NETLANDER have been positively evaluated by the International Science and Technical Review Board (ISTRB) at a meeting on March 27-28 scheduled to evaluate the proposals received in response to the NETLANDER payload AO released in November 1999. As a consequence, they are part of the reference payload for phase B. Pre-phase B activities are now starting and we held a very fruitful "Science and payload meeting" on June 26/27 in Paris. All these activities are conducted under the coordination of the European NETLANDER consortium led by France and composed of the main contributors to the NETLANDER programme: France, Finland and Germany. We would like, through this letter, to confirm that CNES will support all the French NETLANDER activities during the coming year and that Phase C is planned to start no later than mid 2001. At that date, all the hardware providers and in particular the US contributions to NEIGE, ATMIS and SEIS should have received firm commitments from their funding agency(ies). Wishing that a joint effort will be successfully implemented, we are looking forward to hearing that your contribution to the three experiments are supported by NASA.

Richard Bonneville Assistant Director for Space Research and Exploration Copies: Jean-Pierre Barriot, PI of the NEIGE experiment Ari-Matti Harri, PI of the ATMIS experiment Philippe Lognonne, PI of the SEIS experiment Veronique Dehant, Co-PI of the NEIGE experiment

CENTRE NATIONAL D'ETUDES SPATIALES Siège Centre de Toulouse 2 place Maurice Quentin - 75039 Paris Cedex 01 18, avenue Edouard Belin - 31401 Toulouse Cedex 4 Tél. : 01 44 76 75 00 / Téléfax 01 44 76 76 76 / Télex 214674 Tél. : 05 61 27 31 31 / Téléfax : 05 61 27 31 79 / Télex : 531081 SIRET 775 665 912 00082 SIRET 775 665 912 00033 RCS PARIS B 775 665 912 - CODE APE 731 Z - N° d'identification TVA : FR 49 775 665 912

NetLander Mars Science Network 55 NetLander Mars Science Network 56 NetLander Mars Science Network 57 NetLander Mars Science Network 58 NetLander Mars Science Network 59 NetLander Mars Science Network 60 NetLander Mars Science Network 61 NetLander Mars Science Network 62 NetLander Mars Science Network 63 APPENDIX 2b: E/PO Letters of Endorsement

NetLander Mars Science Network 64 NetLander Mars Science Network 65 NetLander Mars Science Network 66 NetLander Mars Science Network 67 NetLander Mars Science Network 68 NetLander Mars Science Network 69 NetLander Mars Science Network 70 NetLander Mars Science Network 71 NetLander Mars Science Network 72 NetLander Mars Science Network 73 NetLander Mars Science Network 74 APPENDIX 3: Resumes WILLIAM BRUCE BANERDT Education: University of Southern California (1971-1975), B.S. in Physics (cum laude) Pennsylvania State University (1975-1977) University of Southern California (1977-1983), Ph.D. in Geological Sciences Employment: 1977-83: APT Research Assistant, Jet Propulsion Laboratory, Pasadena 1983-85: National Research Council Resident Research Associate at JPL 1985-1994: Research Scientist, Jet Propulsion Laboratory, Pasadena 1994-present: Lead Scientist, Geophysics and Planetary Geology Element, JPL 1997: Visiting Professor, Institut de Physique du Globe de Paris Professional Activities: 1985-present: Principal Investigator, NASA Planetary Geology and Geophysics 1986-1988: NASA Topographic Science Working Group 1988-1990: Pre–Project Scientist, Mars Global Network/MESUR Mission 1990-1993: MESUR Science Definition Team, Mars Science Working Group 1990-1994: Magellan Guest Investigator, Radar Investigation Team 1992-present: Mars Observer/Mars Global Surveyor Participating Scientist, MOLA (Mars Orbiter Laser Altimeter) Investigation 1993-1994: MESUR Seismometer Instrument Definition Science Team 1994-1996: NASA Planetary Geosciences Review Panel 1994-present Lead Scientist, Geophysics and Planetary Geology Element, JPL 1994-present: JPL Discipline Program Manager, Planetary Geology and Geophysics, Mars Data Analysis, and Cosmochemistry Programs 1995-1996: InterMarsnet Science Definition Team 1995-present: Rosetta Co-Investigator, SESAME (Surface Electrical, Seismic and Acoustic Monitoring Experiment) Investigation 1998-present: NASA Campaign Strategy Working Group: Formation and Dynamics of Earth-like Planets 1999-present: Mars Exploration Program Analysis Group (MEPAG) 2000: Mars ‘03 Orbiter and Scout Science Instrument Definition Team Awards and Honors: Editor's Award for Excellence, Journal of Geophysical Research, 1990 Group Achievement Award, Magellan Radar Science Group, 1992 Group Achievement Award, Mars Observer Mission Operations System Design, 1993 Group Achievement Award, MGS Ground Data System Development Team, 1997 Group Achievement Award, MGS Payload Development Team, 1997 Group Achievement Award, MGS Project Science Team, 2000 Group Achievement Award, MGS MOLA Science Team, 2000 Selected Publications Banerdt, W.B., R.J. Phillips, N.H. Sleep, and R.S. Saunders, Thick shell tectonics on one-plate planets: Applications to Mars, J. Geophys. Res., 87, 9723-9733, 1982. Fanale, F.P., W.B. Banerdt, R.S. Saunders, L.A. Johansen, and J.R. Salvail, Seasonal carbon dioxide exchange between the regolith and atmosphere of Mars: Experimental and theoretical studies, J. Geophys. Res., 87, 10215-10225, 1982. Fanale, F.P., J.R. Salvail, W.B. Banerdt, and R.S. Saunders, Mars: The regolith-atmosphere-cap system and climate change, Icarus, 50, 381-407, 1982. Banerdt, W.B., Support of long wavelength loads on Venus and implications for internal structure, J. Geophys. Res., 91, 403-419, 1986. Banerdt, W.B., and M.P. Golombek, Deformational models of rifting and folding on Venus, J. Geophys. Res., 93, 4759-4772, 1988. Finnerty, A.A., R.J. Phillips, and W.B. Banerdt, Igneous processes and the closed system evolution of the Tharsis region of Mars, J. Geophys. Res., 93, 10225-10235, 1988. Phillips, R.J., N.H. Sleep, and W.B. Banerdt, Permanent uplift in magmatic systems with application to the Tharsis region of Mars, J. Geophys. Res., 95, 5089-5100, 1990.

NetLander Mars Science Network 75 Tanaka, K.L., M.P. Golombek, and W.B. Banerdt, Reconciliation of stress and structural histories of the Tharsis region of Mars, J. Geophys. Res., 96, 15,617-15,633, 1991. Banerdt, W.B., M.P. Golombek, and K.L. Tanaka, Stress and Tectonics on Mars, in Mars, H. Kieffer, B. Jakosky, and C. Snyder, eds., U. of Arizona Press, Tucson, 249-297, 1992. Esposito, P.B., G. Balmino, W.B. Banerdt, B.G. Bills, G.F. Lindal, W.L. Sjogren, M.A. Slade, and D.E. Smith, Gravity and Topography, in Mars, H. Kieffer, B. Jakosky, and C. Snyder, eds., U. of Arizona Press, Tucson, 209-248, 1992. Golombek, M.P., W.B. Banerdt, K.L. Tanaka, and D.M. Tralli, A prediction of Mars seismicity from surface faulting, Science, 258, 979-981, 1992. Banerdt, W.B., and C.G. Sammis, Small–scale fracture patterns on the volcanic plains of Venus, J. Geophys. Res., 97, 16,149-16,166, 1992. Lognonné, P., J. Gagnepain–Beyneix, B. Banerdt, S. Cacho, J.F. Karczewski, and M. Morand, Ultra broad band seismology on InterMarsnet, Planet. Space Sci., 44, 1237-1249, 1996. Banerdt, W.B., R. Abercrombie, S. Keddie, M. Menvielle, H. Mizutani, S. Nagihara, Y. Nakamura, W.T. Pike, Planetary interiors, in Planetary Surface Instrument Workshop, eds. C. Meyer, A.H. Treiman, and T. Kostiuk, LPI Tech. Rept. 95-05, LPI, Houston, 41-50, 1996. Banerdt, W.B., T. Pike, and R. Martin, and P. Lognonné, A seismic investigation of the interior of a comet, Lunar Planet. Sci. XXVII, 59-60, 1996. Banerdt, W.B., G.E. McGill, and M.T. Zuber, Plains tectonics on Venus, in Venus II, U. of Arizona Press, Tucson, 901-930, 1997. Sjogren, W.L., W.B. Banerdt and 7 others, The Venus gravity field and other geodetic parameters, in Venus II, U. of Arizona Press, Tucson, 1125-1162, 1997. Smith, D.E., and 11 others incl. W.B. Banerdt, Topography of the northern hemisphere of Mars from the Mars Orbiter Laser Altimeter, Science, 279, 1686-1692, 1998. Zuber, M.T., and 6 others incl. W.B. Banerdt, Shape of the northern hemisphere of Mars from the Mars Orbiter Laser Altimeter (MOLA), Geophys. Res. Lett., 25, 4393-4396, 1998. Banerdt, W.B., T.C. Duxbury, D.E. Smith, and M.T. Zuber, MOLA ranging observations of Phobos, EOS Trans. Am. Geophys. Un., 79, F526 1998. Zuber, M.T., and 20 others incl. W.B. Banerdt, Observations of the north polar region of Mars from the Mars Orbiter Laser Altimeter, Science, 280, 2053-2060, 1998. Banerdt, W.B., S. Smrekar, J. Ayon, W.T. Pike, and G. Sprague, A low-cost geophysical network mission for Mars, Lunar Planet. Sci. XXIX, Abs.# 1562, 1998. Smith, D.E., and 18 others incl. W.B. Banerdt, The global topography of Mars and implications for surface evolution, Science, 284, 1495-1503, 1999. Harri, A.-M., and 28 others incl. W.B. Banerdt, Network science landers for Mars, Adv. Space Res., 23, 1915-1924, 1999. Banerdt, W.B., and G.A. Neumann, The topography (and ephemeris) of Phobos from MOLA ranging, Lunar Planet. Sci. XXX, Abs.# 2021, 1999. Banerdt, W.B., J.B. Garvin, and G.A. Neumann, MOLA observations of simple impact craters on Phobos, EOS Trans. Am. Geophys. Un., 80, S203, 1999. Banerdt, W.B., and M.P. Golombek, High-resolution stress modeling of the western hemisphere of Mars, EOS Trans. Am. Geophys. Un., 80, F618, 1999. Lognonné, P., and 22 others incl. W.B. Banerdt, The Netlander very broad band seismometer, Planet. Space Sci., in press, 2000. Zuber, M.T., and 14 others incl. W.B. Banerdt, Internal structure and early thermal evolution of Mars from Mars Global Surveyor topography and gravity, Science, 287, 1788-1793, 2000. Banerdt, W.B., and M.P. Golombek, Tectonics of the Tharsis region of Mars: Insights from MGS topography and gravity, Lunar Planet. Sci. XXXI, Abs. # 2038, 2000. Harri, A.-M., and 18 others incl. W.B. Banerdt, Surface Module of the NetLander 2005 Mission, Planet. Space Sci., in press, 2000.

W. Bruce Banerdt

NetLander Mars Science Network 76 NetLander Mars Science Network 77 NetLander Mars Science Network 78 NetLander Mars Science Network 79 NetLander Mars Science Network 80 NetLander Mars Science Network 81 NetLander Mars Science Network 82 William M. Folkner

Present Position Principal Engineer, Jet Propulsion Laboratory, 1998 Simulation System Engineer for Space Interferometer Mission Pre-Project Manager for Laser Interferometer Space Antenna project In Situ Doppler Data Processing Engineer for Mars Sample Return Previous Experience Member of Technical Staff, Jet Propulsion Laboratory, 1988-1998 Research Associate/Assistant at University of Maryland, 1987-1988 Research Assistant at Los Alamos National Laboratory, 1979-1980 EducationBS. in Physics and Mathematics, May 1978, University of New Mexico. MS.. in Physics, December, 1983, University of Maryland. Ph.D. in Physics, August, 1987, University of Maryland. Dissertation title Analysis and Development of a Three-Mode Gravitational Radiation Detector Current Research Planetary and solar system dynamics Planetary atmosphere dynamics Mars Pathfinder Participating Scientist Space-based gravitational wave detection Memberships American Geophysical Union American Astronomical Society Relevant Publications Golombek MP, Anderson RC, Barnes JR, W.M. Folkner, et al., Overview of the Mars Pathfinder Mission: Launch through landing, surface operations, data sets, and science results, J. Geophysical Research 104, 8523-8553, 1999. W. M. Folkner, R. Woo, and S. Nandi, Ammonia abundance in Jupiter's atmosphere derived from the attenuation of the Galileo probe’s radio signal , JGR-Planets 103, 22847-22855, 1998 W. M. Folkner, C. F. Yoder, D. N. Yuan, E. M. Standish, R. A. Preston, Interior structure and seasonal mass redistribution of mars from radio tracking of Mars Pathfinder, Science 278 1749-1752, 1997 M. P. Golombek, R. A. Cook, T. Economou, W. M. Folkner, A. F. C. Haldemann, et al., Overview of the Mars Pathfinder mission and assessment of landing site predictions, Science 278, 1743-1748, 1997 R. T. Stebbins, P. L. Bender, W. M. Folkner, Getting astrophysical information from LISA data, Classical and Quantum Gravity 14, 1499-1505, 1997 W. M. Folkner, F. Hechler, T. H. Sweetser, M. A. Vincent, P. L. Bender, LISA orbit selection and stability, Classical and Quantum Gravity 14, 1405-1410, 1997 W. M. Folkner, R. D. Kahn, R. A. Preston, C. F. Yoder, E. M. Standish, J. G. Williams, C D. Edwards, R. W. Hellings, T. M. Eubanks, B. G. Bills, Mars dynamics from Earth-based tracking of the Mars Pathfinder lander, J. Geophysical Research, 102, 4057-4064, 1997. W. M. Folkner, R. A. Preston, J. S. Border, J. Navarro, W. E. Wilson, M. Oestreich, Earth-based radio tracking of the Galileo probe for Jupiter wind estimation, Science, 275, 644-646, 1997. R. T. Stebbins, P. L. Bender, W. M. Folkner, LISA data acquisition, Classical and Quantum Gravity, 13, A285-A289, 1996. W. M. Folkner, T. P. McElrath, and A. J. Mannucci, Determination of position of Jupiter from very long baseline interferometry observations of Ulysses, Astronomical Journal 112, 1294-1297, 1996. W. M. Folkner, P. Charlot, M. H. Finger, J. G. Williams, O. J. Sovers, X X Newhall, and E. M. Standish, Determination of the extragalactic-planetary frame tie from joint analysis of radio interferometric and lunar laser ranging measurements, Astron. Astrophys. vol. 287, pp. 279-289, 1994.

NetLander Mars Science Network 83 NetLander Mars Science Network 84 NetLander Mars Science Network 85 CHARLES F. YODER EDUCATION: BA. Physics, U.C. Santa Barbara (1968) Ph.D. Physics, U.C. Santa Barbara (1973) Thesis: On the Establishment and Evolution of Orbit-Orbit Resonance EXPERIENCE: 1973-1976: UCLA, University of California, Los Angeles Assistant Research Geophysicist 1976-present Jet Propulsion Laboratory, Pasadena, CA Member of Technical Staff PRESENT TASKS: Dynamical studies including lunar resonance locks, tidal evolution, planetary wobbles and fluid core-mantle coupling. Analysis of Earth Rotation, post-glacial rebound. PROFESSIONAL MEMBERSHIPS: AAS Division on Dynamical Astronomy American Geophysical Union International Astronomical Union PUBLICATIONS Yoder, C.F., (1973) On the Establishment and Evolution of Orbit-Orbit Resonances. Thesis, University of California, Santa Barbara. Kuala, W. M. and Yoder, C.F., (1976) Lunar Orbit Evolution and Tidal Heating of the Moon. Lunar Science, VII, Houston, TX. Yoder, C.F., (1977) Effects of the Spin-Spin Interaction and the Inelastic Tidal Deformation on the Lunar Physical Libration in Natural and Artificial Satellite Notation. Edited by P. Nacozy and S. Ferrez-Mello, University of Texas, Press, 211-221. Yoder, C.F., Sinclair, W.S.. and Williams, J.G., (1978) The Effects of Dissipation in the Moon on the Lunar Physical LIbration. Lunar Sciences, IX Houston, TX. Williams, J. G., Sinclair, W. S., and Yoder, C.F. (1978) Tidal Acceleration of the Moon. Geophys. Res. Letters, 5, 943. Yoder, C.F., (1978) Free Motion of the Earth’s Inner Core. EOS, 59, 1123. Yoder, C.F., and Ward, W.R., (1978) Does Venus Wobble? BAAS, 10, 543. Yoder, C.F., (1979a) Diagrammatic Theory of Transition of Pendulum-like Systems. Celestial Mechanics, 19, 3-29. Yoder, C.F., (1979b) How Tidal Heating in Io Drives the Galilean Orbital Resonance Locks. Nature, 279, 747-770. Yoder, C.F. (1979c), Notes on the Origin of the Trojan Asteroids. Icarus, 40, 341-344. Yoder, C.F., (1979d), Consequences of Joule Heating Versus Tidal Heating of Io., BAAS, 11, 599. Yoder, C.F., and Ward, W.R. (1979). Does Venus Wobble? Ap. J. Letters, 233, L33-L37.. Ferrari, A.J., Sinclair, W.S., Sjogren, W.L. Williams, J.G., and Yoder, C.F. (1980), Geophysical Parameters of the Earth-Moon System. J. Geophysi. Res., 85, 87, 3939-3951. Stevenson, D.J., and Yoder, C.F. (1981), A Fluid Outer Core for the Moon and Its Implications for Lunar Dissipation. Free Librations and Magnetism, LPSC, XII, Houston, TX 1043. Yoder, C.F. (1981), Tidal Friction and Enceladus’ Anomalous Surface. EOS, 62, 939. Yoder, C.F. (1981) The Free Librations of a Dissipative Moon. Phil. Trans. R. Soc. Lond. A., 3303, 327-338. Yoder, C.F., and Peale, S.J. (1981), The Tides of Io. Icarus, 47, 1-35. Yoder, C. F., Williams, J. G., and Parke, M. E. (1981), Tidal Variations of Earth Rotation. J. Geophys. Res., 86, 881-891.

NetLander Mars Science Network 86 Yoder, C.F. (1981), Effect of Resonance Passage on the Tidal Evolution of Phobos’ orbit. BAAS, 13. Yoder, C.F., Williams, J.G., Parke, M.E., and Dickey, J.O. (1981), Short Period Variations in Earth Rotation. Les Annales de Geophysique, 37, 1, 213-218. Dickey, J.O, Williams, J.G., and Yoder, C.F. (1982), Results from Lunar Laser Ranging Data Analysis. In High Precision Earth Rotation and Earth Moon Dynamics (ed. O.Calame), D. Reidel, Boston, MA 125-137. Yoder, C.F. (1982), The Tidal Rigidity of Phobos. Icarus, 49, 327. Yoder, C.F., Colombo, G., and Synnott, S.P. (1982), Theory of Motion of Saturn’s Co-orbiting Satellites. Icarus, 53, 431. Yoder, C.F., Williams, J.G. Dickey, J.O., Schutz, B.E., Eanes, R.J., and Tapley, B.D. (1983), Secular Variation of Earth’s Gravitational Harmonic J2 from Lageos and the Nontidal Acceleration of Earth Rotation. Nature, 303, 757- 762. Nash, B.D., Carr, M.H., Gradie, J., Hunten, D.M., and Yoder, C.F. (1984), Io. In Nature Satellites (ed. J.A. Burns and D. Morrison), U. of Arizona Press. Yoder, C.F., and Ivins, E.R. (1986), On the Elliptically of the Core Mantle Boundary from Earth Nutations and Gravity. To appear in Proc. of IAU Symposium, 128: Earth Rotation and Reference Frames for Geodesy, A.K. Babcock and G. A. Wilkens (eds.), 317-322. Yoder, C.F., and Ivins, E.R. (1987), Improved Analytic Nutation Model, Proc. of IAU Symp. No. 129: Impact of VLBI on Astrophysics and Geophysics, Cambridge, MA. Salo, H., and Yoder, C.F. (1988), Dynamics of Co-Orbital Satellite Rings. Proc. of IAU Coll. No. 96: The Few Body Problem., M.J. Valtonen (ed.), Kluwer Acad., Dordrecht, 179-184. Salo, H., and Yoder, C.F. (1988), Dynamics of Co-Orbital Satellite Systems, Astron. Astrophysics., 205, 309-327. Slade, M.A and C.F. Yoder (1989) 1960 Chile: New Estimate of Polar Motion Excitation, Geophys. Res. Lett, 16, 1193-1196. Yoder, C.F., Synnott, S.J., and Salo, H. (1989), Orbits and Masses of Saturn’s Coorbiting Satellites, Astron. J, 98, 1875-1889. Ivins, E. and C.F. Yoder (1990) Solid Tide Deformations and Gravity at Diurnal and Semi-diurnal Frequency for Earth Modules with Lateral Variations in Seismic Velocity, EOS. Borderies, N., and Yoder, C.F. (1990), Phobos’ Gravity Field and its Influence on its Orbit and Physical Librations. Astron. Astrophys. Ivins, E.R., and C.G. Sammis, C.F. Yoder, (1993) Deep Mantle Viscous Structure with Prior Estimate and Satellite Constraint, J. Geophys. Res., 98, 4579-4611. Yoder, C.F. (1993) Connections Between Venus’ Free Obliquity and CMB Oblateness, LPSI XXIV, pt.3, 1561. Yoder, C.F. (1994) The Astrometric and Geodetic Properties of Earth and the Solar System, in Global Earth Physics: Handbook of Physical Constants, AGU publication. Dickey, J.O., P.L. Bender, J.E. Faller, XX Newhall, R.L. Ricklefs, J. G. Ries, P.J. Shelas, C. Veillet, A.L. Whipple, J.R. Wiant, J.G. Williams and C.F. Yoder, (1994) Lunar Laser Ranging: A Continuing Legacy of the Apollo Program, Science, 265, 482-490. Yoder, C.F. (1995) Venus’ Free Obliquity, Icarus 117, 250-286. Konopliv, A.S., Yoder C.F. (1996), Venusian k(2) tidal Love number from Magellan and PVO tracking data, Geophys. Res. Lett. 23, 1857-1860. Yoder, C.F., Standish, E.M. (1997), Martian precession and rotation from Viking lander range data, J. Geophys. Res. 102, 4065-4080 W. M. Folkner, W. M., Yoder, C. F., Yuan, D. N., Standish, E. M., Preston, R. A. (1997), Interior structure and seasonal mass redistribution of mars from radio tracking of Mars Pathfinder, Science 278 1749-1752 Folkner, W. M., Kahn, R. D., Preston, R. A., Yoder, C. F., Standish, E. M., Williams, J. G., Edwards, C D., Hellings, R. W., Eubanks, T. M., Bills, B. G. (1997), Mars dynamics from Earth-based tracking of the Mars Pathfinder lander, J. Geophys. Res., 102, 4057-4064

NetLander Mars Science Network 87 NetLander Mars Science Network 88 NetLander Mars Science Network 89 NetLander Mars Science Network 90 NetLander Mars Science Network 91 NetLander Mars Science Network 92 NetLander Mars Science Network 93 NetLander Mars Science Network 94 NetLander Mars Science Network 95 SIMON B. CALCUTT Oxford University, Department of Physics, Atmospheric, Oceanic and Planetary Physics,

Dr. Calcutt is the ATMIS Co-PI responsible for integrating the ATMIS and ELF sensors with the ATMIS/ELF Boom and will also take the responsibility for integrating the JPL-supplied wind and temperature sensors on this boom.

Dr. Calcutt is the Head of Planetary Experiments in the Department of Atmospheric, Oceanic and Planetary Physics at the University of Oxford. His scientific expertise is mainly in the area of radiative transfer. He is a Co-Investigator on the Near Infrared Mapping Spectrometer (NIMS) on Galileo. Dr. Calcutt was a Co-Investigator on the Eureca Occultation Radiometer experiment on the ESA, European Retrievable Carrier which was launched in 1992. He had overall responsibility for the design, manufacture and data analysis from the infra-red half of this instrument which measures water vapour abundance in the stratosphere and mesosphere. He was a Co-Investigator on the Pressure Modulator Infrared Radiometer (PMIRR) instruments which were lost on Mars Observer and Mars Climate Orbiter. He had responsibility for delivery of the UK contributed hardware. He is also a Co-Investigator on the Composite Infrared Spectrometer (CIRS) on Cassini, once again with responsibility for delivery of the UK part of the instrument. He was a member of the ESA/NASA Joint Science Working Group for the definition of the Cassini Spacecraft and from 1989 to 1992 was a member of the ESA Solar System Working Group.

SELECTED PUBLICATIONS Kamp, L.W., F. W. Taylor and S. B. Calcutt, Structure of Venus’s atmosphere from modelling of night- side infrared spectra. Nature, 336, 360, 1988. Taylor, F.W., L. W. Kamp and S. B. Calcutt, High latitude phenomena, Deep Cloud Structure, and Water vapour on Venus. Adv. Space Research, 10, 5, 47, 1990. Carlson, R. W., K. H. Baines, Th. Encrenaz, F. W. Taylor, P. Drossart, L. W. Kamp, J. B. Pollack, E. Lellouch, A. D. Collard, S. B. Calcutt, D. Grinspoon, P. R. Weismann, W. D. Smythe, A. C. Ocampo, G. E. Danielson, F. P. Fanale, T. J. Johnson, H. H. Keiffer, D. L. Matson, T. B. McCord, and L. A. Soderblom, Galileo Infrared Imaging Spectroscopy Measurements at Venus. Science, 253, 1541, 1991. Calcutt, S.B., T. M. Pritchard, . L. Hepplewhite, F. W. Taylor, S. T. Werrett, E. Arijs and D. Nevejans, A Radiometer for the Measurement of Water Vapour in the Upper Atmosphere from Space. Applied Optics, 32, 6764, 1993. Strong, K., F. W. Taylor, S. B. Calcutt, J. J. Remedios and J. Ballard, Spectral Parameters for Self- and Hydrogen-Broadened Methane from 2000 to 9500 cm-1 for Remote Sounding of the Atmosphere of Jupiter. J. Quant. Spec. Rad. Trans. 50, 363, 1993. Collard, A.D., F. W. Taylor, S. B. Calcutt, R. W. Carlson, L. W. Kamp, K. Baines, Th. Encrenaz, P. Drossart, E. Lellouch, and B. Bezard, Global Distribution of Carbon Monoxide in the Deep Atmosphere of Venus. Planet. Sp. Science, 41, 487, 1993. Drossart, P., B. Bezard, Th. Encrenaz, E. Lellouch, M. Roos, F. W. Taylor, A. D. Collard, S. B. Calcutt, J. Pollack, D. Grinspoon, R. W. Carlson, K. Baines and L. W. Kamp, Search for spatial variations of the H2O abundance in the lower atmosphere of Venus from Galileo-NIMS. Planet Sp. Sci, 41, 495, 1993. Irwin, P.G.J., P. A. R. Ade, S. B. Calcutt, F. W. Taylor, J. S. Seeley, R. Hunneman, L. Walton, Far Infra- red Resonant Mesh Filter Design for PMIRR. Infrared Physics, 34, 549, 1993. Irwin, P.G.J., S. B. Calcutt and F. W. Taylor, Characterisation of the thermodynamic behaviour of pressure modulated cells for remote sensing of the atmosphere of Mars. J. Quant. Spec. Rad. Trans., 52, 1, 1994. Calcutt, S. B. and F. W. Taylor, The Deep Atmosphere of Venus. Phil. Trans. Roy. Soc. Lond., A 349, 273-283, 1994

NetLander Mars Science Network 96 Roos-Serote, M., P. Drossart, Th. Encrenaz, E. Lellouch, R. W. Carlson, K. H. Baines, F. W. Taylor and S. B. Calcutt, The Thermal Structure and Dynamics of the Atmosphere of Venus between 70 and 90 km from the Galileo-NIMS Spectra. Icarus 114, 300-309, 1995. Roos-Serote, M., P. Drossart, Th. Encrenaz, E. Lellouch, R. W. Carlson, K. H. Baines, F. W. Taylor and S. B. Calcutt, The Thermal Structure and Dynamics of the Atmosphere of Venus between 70 and 90 km from the Galileo-NIMS Spectra. Icarus 114, 300-309 1995. Arijs E., D. Nevejans, D. Fussen, P. Frederick, E. Van Ransbeeck, F. W. Taylor, S. B. Calcutt, S. T. Werrett, C. L. Hepplewhite, T. M. Pritchard, I. Burchell and C. D. Rodgers, The ORA Occultaion Radiometer on Eureca: Instrument description and preliminary results. Adv. Space Res., 316, (8)33, 1995. Taylor F. W., S. B. Calcutt, P. G. J. Irwin, D. J. McCleese, J. T. Schofield, D. O. Muhleman, R. T. Clancy and C. Leovy, Remote sounding of the Martian atmosphere in the context of the InterMarsNet mission: General circulation and meteorology. Planet. Sp. Sci, 44, 1347-1360, 1996. Carlson, R., W. Smythe, K. Baines, E. Barbinis, K. Becker, R. Burns, S. Calcutt, W. Calvin, R. Clark, G. Danielson, A. Davies, P. Drossart, Th. Encrenaz, F. Fanale, J. Granahan, G. Hansen, P. Herrera, C. Hibbitts, J. Hui, P. Irwin, T. Johnson, L. Kamp, H. Kieffer, F. Leader, E. Lellouch, R. Lopes-Gauiter, D. Matson, T. McCord, R. Mehleman, A. Ocampo, G. Orton, M. Roos-Serote, M. Segura, J. Shirley, L. Soderblom, A. Stevenson, F. Taylor, J. Torson, A. Weir and P. Weissman, Near-Infrared Spectroscopy and Spectral Mapping of Jupiter and the Galilean Satellites: Results from Galileo’s Initial Orbit. Science, 274, 385-388, 1996. Irwin, P. G. J., S. B. Calcutt, F. W. Taylor and A. L. Weir, Calculated k distribution coefficients for hydrogen- and self-broadened methane in the range 2000-9500 cm-1 from exponential sum fitting to band-modelled spectra. J.G.R., 101, No E11, 26,137 - 26,154, 1996 Davis, G. R., M. J. Griffin, D. A. Naylor, P. G. Oldham, B. M. Swinyard, P. A. R. Ade, S. B. Calcutt, P. G. J. Irwin, G. S. Orton, D. Gautier, E. Lellouch, T. Encrenaz, T. De Graauw, C. Armand, M. Burgdorf, A. Di Giorgio, D. Ewart, C. Gry, T. Lim, S. Moli nari, M. Price, S. Sidher, A. Smith and D. Texier, ISO LWS measurement of the far-infrared spectrum of Saturn. Astronomy and Astrophysics, 315 L393-396, 1996 Irwin, P. G. J., S. B. Calcutt and F. W. Taylor, Radiative transfer models for Galileo NIMS studies of the atmosphere of Jupiter. Adv. Space. Res. 19, No. 8, 1149-1158, 1997 Irwin, P. G. J., A. L. Weir, S. E. Smith, F. W. Taylor, A. L. Lambert, S. B. Calcutt, P. J. Cameron-Smith, R. W. Carlson, K. Baines, G. S. Orton, P. Drossart, Th. Encrenaz and M. Roos-Serote, Cloud structure and atmospheric composition of Jupiter retrieved from Galileo NIMS Real-time spectra. J.G.R. 103, No E10, 23,001-23,021,1998. Roos-Serote, M, P. Drossart, Th. Encrenaz, E. Lellouch, R. W. Carlson, K. H. Baines, L. Kamp, R. Mehlman, G. S. Orton, S. Calcutt, P. Irwin, F. Taylor and A. Weir, Analysis of Jupiter NEB hot spots in the 4-5 mm range from Galileo/NIMS observations; measurements of cloud opacity, water, and ammonia. J.G.R. 103, No E10, 23,023-23,041,1998. Drossart, P., M. Roos-Serote, Th. Encrenaz, E. Lellouch, K. H. Baines, R. W. Carlson, L. Kamp, G. S. Orton, S. Calcutt, P. Irwin, F.W. Taylor and A. Weir, The solar reflected component in Jupiter’s 5 micron spectra from NIMS/Galileo observations. J.G.R. 103, No E10, 23,043-23,049,1998. Irwin, P. G. J., S.B. Calcutt, K. Sihra, F.W. Taylor, A.L. Weir, J. Ballard, and W.B. Johnston, Band parameters and k coefficients for self-broadened ammonia in the range 4000-11000 cm-1 J. Quant. Spec. Rad. Trans. 62, pp.193-204,1999.

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NetLander Mars Science Network 97 NetLander Mars Science Network 98 NetLander Mars Science Network 99 Curriculum Vitae for James Eugene Tillman Research Professor Department of Atmospheric Sciences (1970--present) University of Washington Seattle, Washington, 98195-1640 Education B.S. Meteorology, Massachusetts Institute of Technology, 1958. M.S. Meteorology, Massachusetts Institute of Technology, 1961. Selected professional responsibilities James Tillman is a Research Professor in the Department of Atmospheric Sciences at the University of Washington. His major areas research include the atmospheric boundary layer of Earth and Mars, triggering of the great Martian dust storms by normal modes, statistical and spectral analyses, and meteorological instrumentation, especially humidity and temperature. With Danish colleagues he published in JAS a comprehensive analysis of Martian high frequency turbulence and average data to infer fluxes, stability and estimate the growth of the convective layer on Mars: this required extending terrestrial models and developing methods to exploit spectral analyses of highly aliased time series. They also demonstrated the universality of turbulent similarity theory. He led the Mars component of the NASA funded K-12 and public “Live from Earth and Mars” project, one component of which was developing his second exhibit in conjunction with the Smithsonian National Air Space Museum, Washington D.C. The Live from Mars Pathfinder meteorology site received more than 10 million hits from more than 2 million sites during July 1997, and, due to its current weather, excellent educational modules, and Mars information, still receives over 50,000 hits/month. During the past 35 years, he has pioneered several in-situ spectroscopic water vapor measurement technologies, including vacuum ultraviolet, infrared and microwave; With colleagues in the Optics/Informatics Dept. of Ris, Danish National Laboratory, Roslikde, Denmark, he developed an infrared, semi-conductor laser based humidity sensor which measures the absorption by one or more spectrally resolved individual water vapor lines over path lengths from centimeters to meters. To first order, the system does not require any calibration other than measuring the path length and roughly the pressure (it can also estimate the pressure) and is insensitve to fog or to water on the optics. Tillman was a member of the Viking Mission to Mars Meteorology Science Team and later developed a unique spacecraft software and support group. His major accomplishments in Martian meteorology include: 1) collecting the first climate record from the surface of another planet, 2) that Martian fronts are quite similar to terrestrial ones, 3) a comprehensive description of the PBL with Danish colleagues, 4) discovering that global dust storms are not annual events, 5) discovering Martian Kelvin waves, which appear to be almost synchronous with the diurnal cycle, and 6) that they might be involved in triggering the great dust storms. He is one of the 6 coauthors of the approximately 100 page Atmospheric Dynamics Chapter of the definitive “Mars” book, 1498 pages, published in 1992 by the University of Arizona Press. With his staff, he collected, edited and produced most of the components of the meteorology climate record from the surface of Mars and deposited them in the NASA PDS and the National Space Science Data Center.

• Invited Co-Investigator NetLander ATMIS, Atmospheric Sciences Program, contributing in science, engineering, operations and outreach activities • Premier contributions to data for and understanding of the boundary layer and climate of Mars • Characterized global dust storm repeatability, proving they were not, as believed, annual process, by developing (including acquiring the last 2 Mars years) the Viking Martian climate pressure record • Pioneered Educational, Public Outreach over the past 25 years • Initiator of the NASA IITA funded “Live from Earth and Mars” presented live Pathfinder meteorology on the web and at the Smithsonian National Air and Space Museum, Washington, DC. • Developed the Permanent ``Viking View of Mars'' exhibit at NASM, 1983-present • NASA 1996 Mars Pathfinder Atmospheric Structures/Meteorology Science Advisory Team • Member of the Viking Meteorology Science Team, making major contributions in instrumentation, science, developing the Mars Climate data base, and the Viking Computer Facility spacecraft Mission operations processing facility

NetLander Mars Science Network 100 • Over 40 years experience developing humidity, temperature, microwave radiometers, computer facilities and mission operations resources for terrestrial and Martian science investigations • Chief Science Advisor: Mission to Mars: A National Traveling Exhibition for Science Education with partial support from NSF of approximately 500,000. Publications J. Polkko, A.-M. Harri, T. Siili, F. Angrilli, S. Calcutt, D. Crisp, S. Larsen, J.P. Pommereau, P Stoppato, A. Lehto, C. Malique, and J. E. Tillman. The NetLander Atmospheric Instrument System (ATMIS): description and performance assessment, (Submitted in June 1999 to Planetary and Space Science) A.-M. Harri 1 , O. Marsal 2 , P. Lognonne 3 , G.W. Leppelmeier 1 , T. Spohn 22 , K.-H. Glassmeier 4 , F. Angrilli 5 , W.B.Banerdt 6 , J.P. Barriot 7 , J.-L. Bertaux 8 , J.J. Berthelier 9 , S. Calcutt 10 , J.C. Cerisier 9 , D. Crisp 6 , et al., and J. E. Tillman 21 and the NetLander Team. ``Network Science Landers For Mars'', Adv. Space Res., Vol 23/11, pp. 1915-24, 1999. Segal, M., R. W. Arritt, and J. E. Tillman ``On the potentia; impact of daytime surface sensible heat flux on the dissipation of Martian cold air outbreaks.'' J. Atmos. Sci, 54, 1544-1549, 1997. Seiff, Alvin, James E. Tillman, James R. Murphy, John T. Schofield, David Crisp, Jeffrey R. Barnes, Clayton LaBaw, Colin Mahoney, John D. Mihalov, Gregory R. Wilson, and Robert Haberle ``The atmospheric structure and meteorology instrument on the Mars Pathfinder lander.''J. Geophys. Res., 102, 4,045-4,056, Feb. 25, 1997. Crisp, D., W. J. Kaiser, T. R. VanZandt, M. E. Hoenk, (JPL) and J. E. Tillman, (University of Washington) ``Micro Weather Stations for Mars'.'' Acta. Astronautica, 35, Supp. 407-415, 1995. Tillman, James E., Lars Landberg and Sren E. Larsen: The Boundary Layer of Mars: Fluxes, Stability, Turbulent Spectra and Growth of the Mixed Layer." J. Atmos. Sci., June 1994, 51, p 1709--1727. J.E. Tillman, N. C. Johnson, P. Guttorp and D. B. Percival: The Martian Annual Atmospheric Pressure Cycle: Years Without Great Dust Storms'', special edition, J. Geophys. Res., June 25, 1993, Vol. 98, No. E6, pp 10,963--10,971. J E.Tillman: Mars Global Atmospheric Oscillations: Annually Synchronized, Transient Normal Mode Oscillations and the Triggering of Global Dust Storms,'' J. Geo.. Res., V93, D8, pp 9433-9451, 1988. J. E. Tillman, R. M. Henry and S. L. Hess: Frontal Systems During Passage of the Martian North Polar Hood Over the Viking Lander 2 Site Prior to the First 1977 Dust Storm,'' J. Geophys. Res.,84, B6, pp 2947-2955, 1979. R. W. Zurek, JPL, J. R. Barnes, OSU, R. M. Haberle and J. B. Pollack, NASA Ames, and J. E. Tillman and C. B. Leovy, UW: Mars. Chapter 26 {Dynamics of the Atmosphere Mars} , 835-933; Tillman's contribution is the Viking Lander environment, the Planetary Boundary Layer, global normal mode oscillation discoveries and other elements, 9 pages, 8 figures, 1 color plate 44 references., H. H Kieffer et al. Eds, 1498 pages, Oct 1992, University of Arizona Press. Leovy, C. B., J. E. Tillman, W. R. Guest and J. Barnes: Interannual Variability of Martian Weather, Recent Advances in Planetary Meteorology,'' ed. Garry Hunt, Proceedings of Seymour Hess Memorial Symposium, IUGG Hamburg 1983, Cambridge University Press, pp. 69-84, 1985. J. E. Tillman: Martian Meteorology and Dust Storms from Viking Observations,'' pp. 333-342, Proceedings of The Case for Mars II conference, Boulder Colo., July 1984, Christopher P. McKay, ed, Vol 62, Science and Technology Series American Astronautical Society, San Diego, CA 1985. Hess, S. L., J. A. Ryan, J. E. Tillman, R. M. Henry and C. B. Leovy: The Annual Cycle of Pressure on Mars Measured by the Viking Landers 1 and 2,'' Geophys. Res. Let., 7, 197, 1980. Tillman, J. E.: The Indirect Determination of Stability, Heat and Momentum Fluxes in the Atmospheric Boundary Layer from Simple Scalar Variables During Dry Unstable Conditions,'' J. App. Meteor, Vol. 11, pp. 783-792, 1972. Tillman, J. E.: Dynamics of the boundary layer of Mars, in Proceedings of the Symposium on Planetary Atmospheres, pp. 145-149, Royal Society of Canada, Ottawa, Ontario, Canada, 1977.

NetLander Mars Science Network 101 APPENDIX 4: Compliance with U.S. Export Laws and Regulations The JPL Mars NetLander Discovery Mission of Opportunity proposal requests funding for 3 instruments: ATMIS, NEIGE, and SEIS. The NetLander mission is organized by the NetLander Consortium, an international group described in the NetLander AO: The NETLANDER programme is conducted in a European and international co- operative framework under the leadership of the French CNES. The NETLANDER Consortium is composed of members that have made technical contributions both at the system and instruments level. As of the date of this Announcement, the Consortium members are France (CNES), Finland (FMI), Germany (DLR) and Belgium (SSTC). Responsibilities of each organization (including NASA, if funding is received) with respect to the NetLander mission will be finalized in an interagency Memorandum of Understanding currently being drafted between NASA and CNES. This MOU will describe not only the hardware to be delivered, but also the delivery phasing, location, and eventual integration point for each instrument. In its current form, the international agreement specifies the following: The ATMIS instrument includes 3 atmospheric temperature sensors and a wind sensor. The sensors will be initially delivered to Oxford University, England, and their electronics will be delivered to the Finnish Meteorological Institute, Finland. NEIGE is a geodesy experiment, and the JPL portion is a dual-band Doppler receiver that will be incorporated onto a Mars orbiter, probably by CNES (the orbiter has not yet been identified). For SEIS JPL will provide a short- period seismometer that will be delivered to CNES. Final integration of all instruments will occur in France (by CNES), and the integrated spacecraft will be shipped to French Guyana for launch on an Ariane 5 platform. In addition to hardware deliveries, there will be discussions with colleagues in Europe involving algorithms for analysis of the data, but all of the relevant material is available in the open literature, and thus should not be subject to export control restrictions. Our expectation is that export licenses will be required for all flight hardware, while test equipment returning to the U.S. would not require this license. Applications for the export licenses would begin immediately upon selection of this proposal for funding (anticipated 12/00), allowing at least one year for the license process before the Engineering Model delivery is due. However, the Engineering Model may return to the U.S. within 4 years, and thus might not require an export license. The first flight hardware delivery date is May 2002. If the funding decision is made early in 2001, we do not anticipate that the export license process will affect our delivery schedule.

NetLander Mars Science Network 102 APPENDIX 5: Outline of Technical Responsibilities between U.S. and International Partners U.S. participation in the NetLander Mission, including science objectives, requirements, and schedule, is described in the NetLander Discovery Mission of Opportunity Proposal, dated August 1, 2000. This outline describes the responsibilities of the Jet Propulsion Laboratory (JPL) and the U.S. portion of the NetLander Team, as well as their international partners. Note that NASA and CNES are currently drafting an Memorandum of Understanding which describes the responsibilities of all parties in the NetLander collaboration, and that the responsibilities outlined in that document will supercede those described here, should discrepancies between the two documents occur. A consortium of international agencies will implement the NetLander mission. It is managed by the Centre National d'Etudes Spatiales (CNES) of France. The other institutions are Ilmatieteen Laitos (the Finnish Meteorological Institute, FMI), and Deutschen Zentrum für Luft und Raumfahrt (German Space Agency, DLR). The NetLander Mission will be launched in 2005 on an Ariane V, with the CNES Mars Orbiter. Several days prior to arrival at Mars, the landers will be separated from the carrier spacecraft and targeted to locations on the Martian surface. During the baseline mission of one Martian year, the payloads will conduct simultaneous seismological, electromagnetic, atmospheric, ionospheric, and geodetic measurements, as well as ground penetrating radar sounding and panoramic imaging. These data will be combined with simultaneous observations from the planned Mars Express Orbiter. Data uplink and downlink services for all experiments will be funded by the NetLander Consortium, with the exception of the NEIGE experiment, which has costed it own DSN time in this proposal, should that be necessary. JPL will contribute hardware and analysis support for three experiments on the NetLander Project: ATMIS, SEIS, and NEIGE. These experiments are part of an international collaboration to send four landers to Mars, and will be integrated into the spacecraft and launched by the Centre National d’Etudes Spatiales (CNES). JPL's responsibilities include: a. Assisting the international NetLander Team in (1) assessing the mission's feasibility, (2) developing programmatic constraints and trade-off criteria, and (3) establishing a Science Team to refine the Science Requirements, Mission Design, and Science Analysis Plan, b. Specific to ATMIS (ATmospheric Meteorological Instrumentation System): design, build, and test a wind sensor and temperature sensors for operation on the Mars surface, deliver the products to Oxford University for integration onto the ATMIS/ELF boom, provide integration and test support, and science analysis and operations support after launch, c. Specific to NEIGE (NetLander Ionosphere and Geodesy Experiment): design, build, and test a dual-band Doppler receiver for operation in the Martian orbital environment, deliver the product to CNES for integration onto the orbiter, provide integration and test support, and science analysis and operations support after launch, d. Specific to SEIS (NetLander SEISmometer): design, build, and test short-period seismometers for operation in the Martian environment (four such systems will be built), deliver the seismometer systems to CNES for integration onto the landers, provide integration and test support, and science analysis and operations support after launch, e. Providing day-to-day management and coordination of the U.S. portion of the Project as delegated by the PI, including monitoring and reporting technical progress and financial status, and performing a Preliminary Design and Phase C/D/E Review, a Critical Design Review, and a Pre-ship Readiness Review.

NetLander Mars Science Network 103 APPENDIX 6: Compliance with Procurement Regulations by NASA PI Proposals The NetLander PI is not a NASA employee, and thus this section is Not Applicable to the NetLander Proposal.

NetLander Mars Science Network 104 APPENDIX 7: Acronyms List ADC: Analog to Digital Converter AH: Ad Hoc (data format) ALERT: Augmented Learning Environment and Renewable Teaching ARC: Ames Research Center ATMIS: Atmospheric and Meteorological Instrumentation System ASI: Atmospheric Structure Investigation CDR: Critical Design Review CM: Center of Mass CMDS: Command and Data Management System CMOS: Complementary Metal Oxide Semiconductor CNES: Centre National d’Etudes Spatiales (French Space Agency) COMPLEX: Committee on Planetary and Lunar Exploration DA: Data Analysis DAP: Data Analysis Program DLR: Deutschen zentrum für Luft und Raumfahrt (German Space Agency) DORIS: Doppler Orbitography and Radiopositioning Integrated by Satellite DRIE: Deep Reaction Ion Etching DSN: Deep Space Network EDLS: Entry, Descent, and Landing System ELF: Electric Field (Experiment) EMC: Electromagnetic Compatibility E/PO: Education and Public Outreach ESA: European Space Agency ESO: European Southern Observatory FCN: Free Core Nutation FIFO: First In First Out FIST: Facility Instrument Science Team FMEA: Failure Mode and Effect Analysis FMI: Ilmatieteen Laitos (Finnish Meteorological Institute) FDSN: Federation of Digital Seismic Networks GCM: General Circulation Model HASI: Huygens Atmospheric Structure Instrument HBCU/MI: Historically Black Colleges and Universities/Minority Institutions HF: High Frequency HRCR: Hardware Record Certification Review (pre-ship review) IB: Isothermal Block IM: Instrument Manager IMEWG: International Mars Exploration Working Group IPG: Institut de Physique du Globe IPGP: Institut de Physique du Globe, Paris JPL: Jet Propulsion Laboratory K: Kelvin LFEM: Live From Earth and Mars LMD: Laboratoire de Meteorologie Dynamique LOD: Length of Day

NetLander Mars Science Network 105 LF: Low Frequency LP: Long Period MESUR: Mars Environmental Survey MET: Meteorological experiment MGCM: Mars General Circulation Model MGS: Mars Global Surveyor MO: Mission Operations MOU: Memorandum of Understanding MPF: Mars PathFinder MPL: Mars Polar Lander MSSS: Malin Space Science Systems MVACS: Mars Volatiles and Climate Surveyor NASDB: National Association of Small Disadvantaged Business NEIGE: NetLander Ionosphere and Geodesy Experiment NGR: NEIGE Geodetic Receiver NMO: NASA Management Office OPTIMISM: Mars 96 seismic experiment (French) OSS: Office of Space Science PDR: Preliminary Design Review PDS: Planetary Data System PM: Project Manager PRT: Platinum Resistance Thermometer PSP: Participating Scientist Program SAC: Seismic Analysis Code SB: Small Business SBA: Small Business Administration SDB: Small Disadvantaged Business SEED: Standard for the Exchange of Earthquake Data SEIS: NetLander Seismometer SJ: Sense Junction (thermocouple) SMA: Safety and Mission Assurance SNC: Shergotty Nakhla Chassigny – type meteorites (from Mars) SP: Short Period SSTC: Services fédéraux des affaires Scientifiques Techniques et Culturelles (Belgium) STA/LTA: ratio of the Short Term Average over the Long Term Average TC: ThermoCouple TEM: Temperature of Earth and Mars UBB: Ultra Broad Band UHF: Ultra High Frequency UT: Universal Time UTC: Coordinated Universal Time UW: University of Washington VBB: Very-Broad Band WOB: Woman-Owned Business

NetLander Mars Science Network 106 APPENDIX 8: References SEIS: Anderson, D. L., W. F. Miller, G. V. Latham, Y. Nakamura, M. N. Toksöz, A. M. Dainty, F. K. Duennebier, A. R. Lazarewicz, R. L. Kovach, and T. C. D. Knight, 1977. Seismology on Mars. J. Geophys. Res. 82:4524- 4546. Banerdt, B., A. F. Chicarro, M. Coradini, C. Federico, R. Greeley, M. Hechler, J. M. Knudsen, C. Leovy, Ph. Lognonné, L. Lowry, D. McCleese, C. McKay, R. Pellinen, R. Phillips, G. E. N. Scoon, T. Spohn, S. Squyres, F. Taylor, and H. Wänke, 1996. INTERMARSNET Phase–A Study Report. EAS Publ. D/SCI(96)2, 158 pp. Duennebier, F., and G. H. Sutton, Thermal moonquakes, 1974. J. Geophys. Res. 79:4351-4363. Gault, D. E., and B. S. Baldwin, 1970. Impact cratering on Mars – Some effects of the atmosphere (abs.). EOS Trans. Am. Geophys. Un. 51:343. Goins, N. R., and A. R. Lazarewicz, 1979. Martian seismicity. Geophys. Res. Lett. 6:368-370. Golombek, M. P., W. B. Banerdt, K. L. Tanaka, and D. M. Tralli, 1992. A prediction of Mars seismicity from surface faulting, Science 258:979-981. Helmberger, D. and R.A. Wiggins, 1971. J. Geophys. Res. 76:3229-3295. Langston, C., 1981. J. Geophys. Res. 86:3857-3866. Lognonné, P., and B. Mosser, 1993. Planetary Seismology. Surv. Geophys., 14:239-302. Lognonné, P., J. Gagnepain–Beyneix, W. B. Banerdt, S. Cacho, J. F. Karczewski, and M. Morand, 1996. Ultra broad band seismology on InterMarsnet. Planet. Space Sci., 44:1237-1249. Moquet, A., 1999. A search for the minimum number of stations needed for seismic networking on Mars, Plan. Space Science, 47,397-409. Nakamura, Y., G. V. Latham, H. J. Dorman, 1982. Apollo lunar seismic experiment–Final summary. Proc. Lunar Planet. Sci. Conf. 13th, Part 1, J. Geophys. Res., Suppl. 87:A117-A123. Nakamura, Y., 1989. A method for dynamic characteristics estimation of subsurface using microtremors on the ground surface. Quart. Rept. Railway Tech. Res. Inst., Japan 30:25-33. Solomon, S. C., D. L. Anderson, W. B. Banerdt, R. G. Butler, P. M. Davis, F. K. Duennebier, Y. Nakamura, E. A. Okal, and R. J. Phillips, 1991. Scientific Rationale and Requirements for a Global Seismic Network on Mars. LPI Tech. Rept. 91-02, Lunar and Planetary Inst., Houston, 83 pp. NEIGE: Bertka, C.M. and Y. Fei, 1998, Implication of Mars Pathfinder Data for the accretion history of the terrestrial planets. Science, 281, pp. 1838-1840. Boehler, R., 1992, Melting of the Fe-FeO and Fe-FeS systems at high-pressure constraints on core temperatures. Earth Planet. Sci. Lett., 111, pp. 217-227. Bouquillon X. and Souchay J., 1996. Nutation of the planet Mars. Astron. Astrophys., 345, pp. 282. Defraigne, P., V. Dehant, and T. Van Hoolst, 1999a, Steady state convection constrained by Tharsis, the geoid and the precession constant., Phys. Earth planet. Inter., in preparation. Defraigne, P., O. de Viron, V. Dehant, T. Van Hoolst, and F. Hourdin, 1999b, Mars rotation variations induced by atmosphere and ice caps. J. Geophys. Res., in preparation. Dehant, V., P. Defraigne, and T. Van Hoolst, 1999a, Computation of Mars' transfer function for nutation tides and surface loading., in: Proc. SEDI meeting, Session 8: `Deep interior of terrestrial planets', Tours, France, July 1998, Phys. Earth planet. Inter., accepted. Dehant, V., P. Defraigne, and T. Van Hoolst, 1999b, Comparison between the nutations of the planet Mars and the nutations of the Earth. Geophys. Survey, submitted.

NetLander Mars Science Network 107 Dehant, V., Roosbeek F., Van Hoolst T., and Barriot J.-P., 1999c, A strategy to determine geophysical parameters from Mars' orientation. Planet. Space Sc., in preparation. Dehant, V., de Viron O., and Van Hoolst T., 1999d, Effects of triaxiality on the rotational normal modes and polar motion of the Earth and the planet Mars. Geophys. Res. Letters, in preparation. Dehant, V., Defraigne P., de Viron O., and Van Hoolst T., 1999e, The Free Inner Core Nutation of the planet Mars. In preparation. Folkner, W.M., R.D. Kahn, R.A. Preston, C.F. Yoder, E.M. Standish, J.G. Williams, C.D. Edwards, and R.W. Hellings, 1997, Mars dynamics from Earth-based tracking of Mars Pathfinder lander. J. Geophys. Res., 102, pp. 4057-4064. Longhi, J., E. Knittle, J.R. Holloway, and H. Wänke, 1992, The bulk composition, mineralogy and internal structure of Mars. In: `Mars', eds. H. H. Kieffer, B.M. Jakosky, C.W. Snyder, and M.S. Matthews, Univ. Arizona Press, Tucson, Arizona, pp. 184-207. Roosbeek, F., 1999, Analytical developments of rigid Mars nutation and tide generating potential. Celest. Mech., submitted. Schubert, G. and T. Spohn, 1990, Thermal history of Mars and the sulfur content of its core. J. Geophys. Res., 95, pp. 14,095-14,104. Schubert, G., S.C. Solomon, D.L. Turcotte, M.J. Drake, and N.H. Sleep, 1992, Origin and thermal evolution of Mars. In: `Mars', eds. H.H. Kieffer, B.M. Jakosky, C.W. Snyder, and M.S. Matthews, Univ. Arizona Press, Tucson, Arizona, pp. 147-183. Sohl, F. and T. Spohn, 1997, The interior structure of Mars: implications from SNC meteorids. J. Geophys. Res., 102, pp. 1613-1636. Sotin, C., S. Labrosse, and A. Mocquet, 1996, Nusselt-Rayleigh relationship for a fluid heated from below and from within: application to the cooling rate of the Martian core., in: Proc. Lunar Planet. Sci. Conf. 27th, Houston, pp. 1247-1248. Smith, D. E., F. J. Lerch, R. S. Nerem, M. T. Zuber, G. B. Patel, S. K. Fricke, and F. G. Lemoine, 1993, "An improved gravity field for Mars: Goddard Mars Model 1", J. Geophys. Res. 98, 20871-20889 Van Hoolst, T., Dehant V., and Defraigne P., 1999a, Sensitivity of the Free Core Nutation and the Chandler Wobble to changes in the interior structure of Mars. In: Proc. SEDI meeting, Session 8: `Deep interior of terrestrial planets', Tours, France, July 1998, Phys. Earth planet. Inter., accepted. Van Hoolst, T., Dehant V., and Defraigne P., 1999b, Chandler Wobble and Free Core Nutation for Mars. Planet. Space Sc., submitted. Yoder, C.F. and Standish E.M., 19997, Martian precession and rotation from Viking lander range data. J. Geophys. Res., 102(E2), pp 4065-4080. Zharkov, V.N., E.M. Koshlyakov, and K.I. Marchenkov, 1991, Composition, structure and the gravity field of Mars. Solar System Res., 25, pp. 515-547

ATMIS: Bougher S, G. Keating, and R. Zurek, J. Murphy, R. Haberle, J. Hollingsworth, R. T. Clancy, 1999, “Mars Global Surveyor aerobraking: Atmospheric trends and model interpretation”, Moon and Mars, 23, 1887- 1897. Haberle R. M., M. M. Joshi, J. R. Murphy, J. R. Barnes, J. T. Schofield, G. Wilson, M. Lopez-Valverde, J. L. Hollingsworth, A. F. C. Bridger, J. Schaeffer, 1999, “General circulation model simulations of the Mars Pathfinder atmospheric structure investigation/meteorology data,” J. Geophys. Res. 104, 8957-8974. Magalhaes J.A., J. T. Schofield, A. Seiff, 1999, “Results of the Mars Pathfinder atmospheric structure investigation,” J. Geophys. Res., 104, 8943-8955. Schofield, J. T., J. R. Barnes, D. Crisp, R. M. Haberle, S. Larsen, J. A. Magalhães, J, R. Murphy, A. Seiff, and G. Wilson, 1997, “The Mars Pathfinder atmospheric structure investigation meteorology (ASI/MET) experiment”, Science, 278, 1752-1758.

NetLander Mars Science Network 108 Segal, M., R. W. Arritt, and J. E. Tillman ``On the potential impact of daytime surface sensible heat flux on the dissipation of Martian cold air outbreaks.'' J. Atmos. Sci, 54, 1544-1549, 1997. Seiff, A. and D. B. Kirk, 1977, “Structure of the atmosphere of Mars in summer at mid latitudes,” J. Geophys. Res. 82, 4364-4378. Seiff, A., J. E. Tillman, J. R. Murphy, J. T. Schofield, D. Crisp, J. R. Barnes, C. LaBaw, C. Mahoney, J. D. Mihalov, G. R. Wilson, and R. Haberle, 1997, “The atmosphere structure and meteorology instrument on the Mars Pathfinder lander”, J. Geophys. Res. 102, 4045-4056. Seiff, A., J.T. Schofield, J.R. Murphy, J.D. Mihalov, 1999, “Winds on Mars at the Pathfinder landing site”, Bull. AAS, 31, 60.02. Tillman, James E., Lars Landberg and Soren E. Larsen, The Boundary Layer of Mars: Fluxes, Stability, Turbulent Spectra and Growth of the Mixed Layer." J. Atmos. Sci., June 1994, 51, p 1709--1727. Zurek, R. W., J. R. Barnes, R. M. Haberle, J. B. Pollack, J. E. Tillman, and C. B. Leovy, 1992, “Dynamics of the atmosphere of Mars,” Mars, University of Arizona Press, 835-933.

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