DOCSLIB.ORG

Orbits That Include Lunar Encounters

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Orbits That Include Lunar Encounters Transfers to L1 and L2 Orbits that Include Lunar Encounters K. C. Howell School of Aeronautics and Astronautics Purdue University School of Aeronautics and Astronautics History: Some Previous Concepts or Missions Involving Lunar Encounters • ISEE-3/ICE • MAP • Double Lunar • Lunar-A Swingbys • Nozomi • Geotail • Hiten • Relict-2 • Genesis • Wind School of Aeronautics and Astronautics Double Lunar Swingbys ISEE-3 Geotail Phase School of Aeronautics and Astronautics WIND Nozomi School of Aeronautics and Astronautics Relict-2 MAP School of Aeronautics and Astronautics Genesis Trajectory Mission •⊕ to L1 / Return •L1 Orbit: Az= 320,000 km Ay=745,000 km •∆V = 8.5 m/s School of Aeronautics and Astronautics Trajectory Design Including Lunar Encounters Apply recent capabilities •Insight? Fast? Efficient? •Target orbit constrained? Timing? •Multiple spacecraft? •New Design Strategies? ⇓ Approaches: Semi-Analytical Numerical School of Aeronautics and Astronautics Direct Transfer: No Encounter Transfer/LOI Small Liss ∆V:LOI 165 -190m/s School of Aeronautics and Astronautics Alternate Solution: No Encounter Single LOI Maneuver ∆V = 95 m/s School of Aeronautics and Astronautics Transfer to L1: Lunar Encounter ∆ VTTI = 3129.43 m/s ∆ VLOI = 2.32 m/s Direct Transfer ∆ VTTI = 3196.69 m/s ∆ VLOI = 185.70 m/s School of Aeronautics and Astronautics Lunar Encounter Phasing Loops ∆V:LOI 21→ 0 m/s School of Aeronautics and Astronautics Trajectory Design Including Lunar Encounters Apply recent capabilities •Insight? Fast? Efficient? •Target orbit constrained? Timing? •Multiple spacecraft? •New Design Strategies? ⇓ Approaches: Semi-Analytical Numerical School of Aeronautics and Astronautics Restricted 4-Body Problem •Natural Dynamics in the Restricted Four-Body Problem •Focus: vicinity of the Moon perturbed Sun-Earth libration points •Computation of nominal orbits •Computation of transfer arcs to the nominal orbits •Shift information to the ephemeris model School of Aeronautics and Astronautics Restricted 4-Body Problem P1 - Sun P2 - Earth P4 - Moon School of Aeronautics and Astronautics Generalized Semi-Analytical Development •Relative EOMs ( wrt P2 ) (M +M ) 4 rrij 2j r +ri2=∑ M- 2i 332i j 3 rrj=1 r 2i ij 2j ji≠ ,2 •Form of the approximation oo oo r=rf ()α r+ˆ f ()βθˆˆ+f (hγ) ,l= 2,j 2i 2l 1 2l 2 2l 3 2l School of Aeronautics and Astronautics Generalized Semi-Analytical Development •Perturbation Approach f(1 α)t +α f(2 β)s +β f(3 γ)z +γ •Trigonometric Series K-1 α =cαα(c) os(ω t)+ (s)sin(ω t) ∑ k=0 kkkk K-1 β =c ββ(c) os(ω t)+ (s)sin(ω t) ∑ k=0 kkkk K-1 γ =cγγ(c) os(ω t)+ (s)sin(ω t) ∑ k=0 kkkk School of Aeronautics and Astronautics Generalized Semi-Analytical Development •Substitute approximation into relative EOMs f1 − 2n2l f2 -3f = U 1 f1 f 2 + 2n2l f1 -3f2 = U f2 f 3 -3f3 = U f3 •Partials are nonlinear functions of f,12f,f3 U=U(f,f,f) ff11123 U=U(f,f,f) ff22123 U=U(f,f,f) ff33123 School of Aeronautics and Astronautics Generalized Semi-Analytical Development • Planar Motion, i.e., γ 2i = 0 and undisturbed: circular motion ⇒ r=roo(1+α )rˆ + βθˆo 2i 2i 2i 2i 2i 2i School of Aeronautics and Astronautics Generalized Semi-Analytical Development •Consider perturbation of libration points r=roo(t+α )rˆ +(s+ βθ) ˆˆo+(z+γ )ho 23 21 23 21 23 21 23 21 •Initial Guess: α23 = β23 = γ 23 =0 •L2 Perturbed School of Aeronautics and Astronautics Generalized Semi-Analytical Development •Consider orbit: same form r=roo(t+α )rˆ +(s+ βθ) ˆˆo+(z+γ )ho 23 21 23 21 23 21 23 21 •Initial Guess: CR3BP Approximations •L2 Orbit Perturbations School of Aeronautics and Astronautics Quasi-Periodic Motion School of Aeronautics and Astronautics Assess Lunar Gravity Impact ∆vfb δ = 2sin−1 2v∞ 2v∞ ∆vfb = 2 1/+ (vQ∞ p µ ) School of Aeronautics and Astronautics Stable Manifold School of Aeronautics and Astronautics Stable Manifold at Lunar Orbit Crossings School of Aeronautics and Astronautics Elongation Angle School of Aeronautics and Astronautics Ephemeris Model: Stable Manifold Transfer Paths Beyond Lunar Orbit School of Aeronautics and Astronautics School of Aeronautics and Astronautics School of Aeronautics and Astronautics School of Aeronautics and Astronautics Lunar Orbit Parameters School of Aeronautics and Astronautics Preliminary Design Procedure • Manifolds: If properly timed, periselene event will occur •Check ΨΨ e − < 5º (Modify tJD (∆t M ), timing condition) •Ephemerides Model: Check season ⇒ Ze •Select Z-e ZS/C <20,000 km •Adjust displacement value “d” to allow finer control (including altitude) •Phasing Loops? •Differentially correct to meet constraints School of Aeronautics and Astronautics Moon Timing Issues -1 β24 (θ) -1 β21(θ) Ψe(θ)=θ +tan -tan (1+ α24 (θ))(1+ α21(θ)) where θ = θo +Nt • Given Time ⇒→θΨclosed form solution →e • Given Elong →→ Ψθe solve transcendental equation School of Aeronautics and Astronautics Manifolds: Asymptotically Approaching Orbit F FWS XX0 =+d Y School of Aeronautics and Astronautics Algorithm: Earth-to-Lissajous Natural Solutions Lissajous Trajectory Case d Value Periselene Altitude Inclination # (km) Elongation (deg) (km) (deg) Orbit S, Class I 47 201.4764 -62.04 186.90 33.47 Orbit S, Class I 141 201.0680 -36.00 196.20 21.12 Orbit S, Class II 134 201.2000 -47.40 699.87 44.35 Orbit T, Class I 52 199.1130 -64.04 183.62 54.91 Orbit T, Class I 138 201.8585 -47.72 182.71 41.19 Orbit T, Class II 64 198.7386 -72.12 184.17 10.07 Orbit T, Class II 134 201.0986 -50.27 183.53 18.35 Corrected Transfer Trajectories Case Name TTI TTI Lunar Lunar LOI Total Date Cost Encounter Altitude Cost Cost (m/s) Date (km) (m/s) (m/s) Orbit S, I, 47 5/20/01 3139.90 6/26/01 17084.52 0.78 3140.68 Orbit S, I, 141 5/22/01 3140.39 7/02/01 11999.28 5.04 3145.43 Orbit S, II, 134 5/22/01 3128.06 7/01/01 36781.55 8.26 3136.32 Orbit L, I, 52 5/21/01 3133.10 6/29/01 15658.84 6.28 3139.38 Orbit L, I, 138 5/21/01 3133.57 7/01/01 14114.37 8.08 3141.65 Orbit L, II, 64 5/20/01 3127.87 6/29/01 17546.67 4.88 3132.75 Orbit L, II, 134 5/22/01 3133.42 6/30/01 15277.15 1.49 3134.91 School of Aeronautics and Astronautics Transfer 1: Lunar Encounter School of Aeronautics and Astronautics Transfer 2 School of Aeronautics and Astronautics Temporary Capture School of Aeronautics and Astronautics Summary •Semi-Analytical: coherent-R4BP •Perturbation approach •Trigonometric series for location of Sun/Moon •Associated invariant manifolds •Identify manifolds bent by the Moon •Approx lunar timing conditions •Numerical Approach: Full Model •Compute nominal orbit (Liss or halo) •Calculate manifolds •Differentially Correct to meet constraints School of Aeronautics and Astronautics R4BP EOMs • Newton’s Equations of Motion X-θ11Y-2θ Y=UX Y+θ11X+2θ X=UY Z=UZ • Pseudo-Potential 1MM M U(X,Y, Z) = θ X+22Y ++1 23+ 1 2r13 r23 r43 • Contrast with CR3BP 1.No integral of the motion 2.No constant equilibrium solutions 3.Symmetries a.Reflection about the X-Y plane b.Reflection about the X-Z plane (with time reversal) IIF primary motion with same symmetry School of Aeronautics and Astronautics Assess Lunar Gravity ∆vfb δ = 2sin−1 2v∞ 2v∞ ∆vfb = 2 1/+ (vQ∞ p µ ) School of Aeronautics and Astronautics Results: Physical Scenario School of Aeronautics and Astronautics Lissajous Orbit: Ay>Az School of Aeronautics and Astronautics Construction of Transfers Using Manifolds School of Aeronautics and Astronautics Transfer 3: Lunar Encounter School of Aeronautics and Astronautics Transfer 4: Lunar Encounter School of Aeronautics and Astronautics Transfer 5: Lunar Encounter School of Aeronautics and Astronautics Transfer 6: Lunar Encounter School of Aeronautics and Astronautics Transfer 7: Lunar Encounter School of Aeronautics and Astronautics Preliminary Design Procedure • Manifolds: Select Z-e ZS/C <20,000 km • “Place” Moon at appropriateΨ e ⇒ non-physical scenarios •Ephemerides Model: Check season ⇒ Ze •Shift to Ephemeris Model School of Aeronautics and Astronautics.
Load more

Recommended publications
  • Gravimetric Missions in Japanese Lunar Explorer, SELENE
    Gravimetric Missions in Japanese Lunar Explorer, SELENE H. Hanada1), T. Iwata2), N. Namiki3), N. Kawano1), K. Asari1), T. Ishikawa1), F. Kikuchi1), Q. Liu1), K. Matsumoto1), H. Noda1), J. Ping4), S. Tsuruta1), K. Iwadate1), O. Kameya1), S. Kuji1), Y. Tamura1), X. Hong4), Y. Aili5), S. Ellingsen6) 1) National Astronomical Observatory of Japan 2) Japan Aerospace Exploration Agency 3) Kyushu University 4) Shanghai Astronomical Observatory, Chinese Academy of Sciences 5)Urumqi Astronomical Observatory,Chinese Academy of Sciences 6) University of Tasmania ABSTRACT SELENE (SElenological and Engineering Explorer), is a mission in preparation for launch in 2007 by JAXA (Japan Aerospace Exploration Agency), it carries 15 missions, two of which (RSAT and VRAD) are gravimetric experiments using radio waves. The RSAT (Relay Satellite Transponder) mission will undertake 4-way Doppler measurements of the main orbiter through the Rstar sub-satellite. This is in addition to 2-way Doppler and ranging measurements of the satellites and will realize the first direct observation of the gravity fields on the far side of the Moon. The VRAD (Differential VLBI Radio Source) mission involves observing the trajectories of Rstar and Vstar using differential VLBI with both a Japanese network (VERA), and an international network. We have already finished development of the onboard instruments and are carrying out proto-flight tests under various conditions. We have also performed test VLBI observations of orbiters with the international network. 1. INTRODUCTION Although it is the nearest astronomical body to the Earth, there are many unsolved problems relating to the origin and the evolution of the Moon. Numerous lunar explorations have been made with the aim of elucidating these problems, however, we still know little of the deep interior of the Moon.
    [Show full text]
  • Protons in the Near Lunar Wake Observed by the SARA Instrument on Board Chandrayaan-1
    FUTAANA ET AL. PROTONS IN DEEP WAKE NEAR MOON 1 Protons in the Near Lunar Wake Observed by the SARA 2 Instrument on Board Chandrayaan-1 3 Y. Futaana, 1 S. Barabash, 1 M. Wieser, 1 M. Holmström, 1 A. Bhardwaj, 2 M. B. Dhanya, 2 R. 4 Sridharan, 2 P. Wurz, 3 A. Schaufelberger, 3 K. Asamura 4 5 --- 6 Y. Futaana, Swedish Institute of Space Physics, Box 812, Kiruna, SE-98128, Sweden. 7 ([email protected]) 8 9 10 1 Swedish Institute of Space Physics, Box 812, Kiruna, SE-98128, Sweden 11 2 Space Physics Laboratory, Vikram Sarabhai Space Center, Trivandrum 695 022, India 12 3 Physikalisches Institut, University of Bern, Sidlerstrasse 5, CH-3012 Bern, Switzerland 13 4 Institute of Space and Astronautical Science, 3-1-1 Yoshinodai, Sagamihara, Japan 14 Index Terms 15 6250 Moon 16 5421 Interactions with particles and fields 17 2780 Magnetospheric Physics: Solar wind interactions with unmagnetized bodies 18 7807 Space Plasma Physics: Charged particle motion and acceleration 19 Abstract 20 Significant proton fluxes were detected in the near wake region of the Moon by an ion mass 21 spectrometer on board Chandrayaan-1. The energy of these nightside protons is slightly higher than 22 the energy of the solar wind protons. The protons are detected close to the lunar equatorial plane at 23 a 140˚ solar zenith angle, i.e., ~50˚ behind the terminator at a height of 100 km. The protons come 24 from just above the local horizon, and move along the magnetic field in the solar wind reference 25 frame.
    [Show full text]
  • FACTORS" with Multiple Compact Satellites for the Space-Earth Coupling Mechanisms
    PCG21-05 Japan Geoscience Union Meeting 2018 Science Objectives and Mission Plan of "FACTORS" with Multiple Compact Satellites for the Space-Earth Coupling Mechanisms *Masafumi Hirahara1, Yoshifumi Saito2, Hirotsugu Kojima3, Naritoshi Kitamura2, Kazushi Asamura 2, Ayako Matsuoka2, Takeshi Sakanoi4, Yoshizumi Miyoshi1, Shin-ichiro Oyama1, Masatoshi Yamauchi5, Yuichi Tsuda2, Nobutaka Bando2 1. Institute of Space-Earth Environmental Research, Nagoya University, 2. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, 3. Research Institute for Sustainable Humanosphere, Kyoto University, 4. Planetary Plasma and Atmospheric Research Center, Graduate School of Science, Tohoku University, 5. Swedish Institute of Space Physics After the successful launch and the recent observational progresses of the ERG(Arase) satellite mission, we have been leading the next community exploration mission in the Japanese space physics research. In the ERG mission, we are focusing on the unique space plasma mechanisms and conditions causing the terrestrial radiation belt through the wave-particle interaction analyses and the triangle-type research system consisting the satellite and ground-based observations and the data analyses/modelings/simulations. Our next exploration target is the space-Earth connection processes/mechanisms responsible for the formation and coupling of the terrestrial magnetosphere/ionoshere/thermosphere and the acceleration and transportation of the space plasma and neutral atmospheric particles, which could be
    [Show full text]
  • Solar System Exploration Strategic Road Map and Venus Exploration
    Solar System Exploration Strategic Road Map and Venus Exploration Presentation at Lunar and Planetary Science Conference James A. Cutts Solar System Exploration Directorate, JPL James R. Robinson Science Missions Directorate, NASA HQ March 16, 2005 03/16/2005 Predecisional - for discussion purposes only 1 Purpose of this briefing • To inform the Venus Science community about the status of the solar system exploration strategic planning process that is currently being carried out by NASA • To seek inputs on future priorities for Venus exploration for inclusion in the nation’s solar system exploration program for input to this process 03/16/2005 Predecisional - for discussion purposes only 2 Strategic Planning and Venus Exploration? • NASA is conducting a strategic planning activity that builds upon the President’s Vision for Space Exploration published in January 2004. • Three Strategic Road Map teams are formulating plans for exploration of the solar system. – Mars Exploration – Lunar Exploration – Solar System Exploration (covering Venus exploration) – co chaired by • Orlando Figueroa (Assoc Director, Science NASA HQ) • Scott Hubbard (Director, ARC) • Jonathan Lunine, University of Arizona and Chair of NASA Solar System Exploration subcommittee • The Solar System Exploration Road Map team is on a very aggressive schedule. It is scheduled to submit its report for review by the National Research Council by June 1, 2005 An important function of this plan will be to guide the NASA investment in new technologies and related capabilities over the next decade. 03/16/2005 Predecisional - for discussion purposes only 3 Strategic Road Map - Solar System Exploration Committee Members • Orlando Figueroa, NASA Science Mission Directorate co-chair G.
    [Show full text]
  • Orbit Determination of the NOZOMI Spacecraft Using Differential VLBI Technique Radio Astronomy Applications Group Kashima Space Research Center IUGG2003, Sapporo
    Orbit Determination of The NOZOMI Spacecraft using Differential VLBI Technique Radio Astronomy Applications Group Kashima Space Research Center IUGG2003, Sapporo (C) ISAS According to the ISAS announcement the NOZOMI has completed its final Earth swingby operation on June 19, and is on its way to Mars. NOZOMI passed within 11,000 km of the NOZOMI Earth in a manuever. (C) ISAS ts Quasar Algonquin (SGL, CRESTech ) tq B: baseline vector Basic Concept of Differential Tomakomai (Hokkaido Univ.) VLBI (DVLBI) observation Mizusawa (NAO) Usuda (ISAS) Gifu Data Sampling Data Sampling (Gifu Univ.) Boards Boards Tsukuba (GSI) K5 VLBI System K5 VLBI System Yamaguchi (Yamaguchi Univ.) Koganei (CRL) Kagoshima(ISAS) Kashima (uplink) (CRL) VLBIVLBI stationsstations participatingparticipating toto DVLBIDVLBI experimentsexperiments Detected NOZOMI fringe Orbit Determination We performed more than 30 differential VLBI (DVLBI) experiments for the NOZOMI spacecraft from September 2002 until June 2003. NOZOMI, which means “Hope” in Japanese, is the Japan's first Mars probe developed and launched by the Institute of Space and Astronautical Science (ISAS). NOZOMI was originally scheduled to reach its destination in October 1998, but an earlier Earth swingby failed to give it sufficient speed, forcing a drastic rescheduling of its flight plan. According to the new trajectory strategy, NOZOMI's arrival at Mars is scheduled early in 2004 through two additional earth swingbys in Dec. 2002 and June 2003. Our main concern was to determine the NOZOMI orbit just before the second earth swingby on June 19, 2003. It was significantly important to get the timing to maneuver the NOZOMI before the swingby. ISAS scientists were afraid that the range and range rate (R&RR) orbit determination might not be available because it was difficult to point the high-gain antenna mounted the spacecraft toward the earth during the period between two swingby events.
    [Show full text]
  • Genomics on the Brain on 9 September, the Father of the Hydrogen Bomb Passed Away
    2003 in context Neuroscience GOODBYE Edward Teller Genomics on the brain On 9 September, the father of the hydrogen bomb passed away. He was a controversial he 1990s may have been designated the creating transgenic mice that carry these figure, who was vilified by many physicists after T‘Decade of the Brain’,but they will also be BACs,the researchers can identify — by sight testifying in 1954 that Robert Oppenheimer, remembered as the time when genomics — the cells in which a gene of interest is nor- leader of the wartime Manhattan Project, was a came to the fore.This year,neuroscience and mally active,and can work out how these cells security risk. Teller later championed President genomics teamed up in projects that promise connect with the rest of the brain. The same Ronald Reagan’s ‘Star Wars’ missile-defence to propel the study of the brain into the realm BACs can also be used to introduce other initiative. But colleagues at the Lawrence of‘big science’. genetic modifications into these cells,provid- Livermore National Laboratory, co-founded by Working on Parkinson’s disease? One of ing a unique tool to investigate their biology. Teller, say that he should also be remembered the projects that surfaced this year might pro- GENSAT’s first images can already be seen for his passion for teaching physics. vide you with a transgenic mouse that offers on its website,which was launched in October fluorescent neurons in key neural pathways. alongside a paper introducing the project Galileo Another could offer you structural brain (S.
    [Show full text]
  • Jjmonl 1907-08.Pmd
    alactic Observer John J. McCarthy Observatory G Volume 12, No. 7/8 July/August 2019 Footprints on the Moon The John J. McCarthy Observatory Galactic Observvvererer New Milford High School Editorial Committee 388 Danbury Road Managing Editor New Milford, CT 06776 Bill Cloutier Phone/Voice: (860) 210-4117 Phone/Fax: (860) 354-1595 Production & Design www.mccarthyobservatory.org Allan Ostergren Website Development JJMO Staff Marc Polansky It is through their efforts that the McCarthy Observatory has established itself as a significant educational and Technical Support recreational resource within the western Connecticut Bob Lambert community. Dr. Parker Moreland Steve Barone Peter Gagne Marc Polansky Colin Campbell Louise Gagnon Joe Privitera Dennis Cartolano John Gebauer Danielle Ragonnet Route Mike Chiarella Elaine Green Monty Robson Jeff Chodak Jim Johnstone Don Ross Bill Cloutier Carly KleinStern Gene Schilling Doug Delisle Bob Lambert Katie Shusdock Cecilia Detrich Roger Moore Jim Wood Dirk Feather Parker Moreland, PhD Paul Woodell Randy Fender Allan Ostergren Amy Ziffer In This Issue "OUT THE WINDOW ON YOUR LEFT" ............................... 4 REFERENCES ON DISTANCES ............................................ 28 APOLLO 11 LANDING SITE ............................................... 5 INTERNATIONAL SPACE STATION/IRIDIUM SATELLITES .......... 28 SATURN AT OPPOSITION ................................................... 6 LAGRANGE POINTS ........................................................ 28 SEARCH FOR SNOOPY .....................................................
    [Show full text]
  • Lems of the Orbit Determination for Nozomi Spacecraft
    November 2001 37 Present status and future prob- lems of the orbit determination for Nozomi spacecraft Makoto Yoshikawa1 ([email protected]), Mamoru Sekido2, Noriyuki Kawaguchi3, Kenta Fujisawa3, Hideo Hanada4, Yusuke Kono4, Hisashi Hirabayashi1, Yasuhiro Murata1, Satoko Sawada-Satoh1, Kiyoaki 1 1 Figure 1. Nozomi spacecraft Wajima , Yoshiharu Asaki , Jun’ichiro Kawaguchi1, Hiroshi Yamakawa1, Takaji Kato1, Tsutomu Ichikawa1, and Takafumi 5 launched several spacecraft that went into inter- Ohnishi planetary space, such as “Sakigake” and “Suisei”. 1 From the point of orbital determination (OD), No- Institute of Space and Astronautical Science zomi is quite different from these previous ones be- (ISAS) cause the requirement for the OD accuracy is much 3-1-1 Yoshinodai, Sagamihara, Kanagawa higher. The maximum distance between Nozomi 229-8510, Japan × 5 2 and the earth is about 5 10 km in the near-earth Kashima Space Research Center phase and about 3 × 108 km in the interplanetary Communications Research Laboratory (CRL) phase. This indicates that the accurate OD is much 893-1 Hirai, Kashima, Ibaraki 314-0012, Japan 3 more difficult in the interplanetary phase than in National Astronomical Observatory (NAO) the near-earth phase. The OD group in ISAS has 2-21-1 Osawa, Mitaka, Tokyo 181-8588, Japan 4 been trying to obtain the much more accurate or- Mizusawa Astrogeodynamics Observatory bit for Nozomi. However, we find that there are National Astronomical Observatory several difficult problems in front of us. We will 2-12, Hoshigaoka, Mizusawa, Iwate 023-0861, mention these problems briefly in the section 4. Japan 5 Up to now (November 2001), there are several Fujitsu Limited events that are very critical to the orbital determi- 3-9-1 Nakase, Mihama-ku, Chiba-shi, Chiba nation of Nozomi.
    [Show full text]
  • Lunar Radar Sounder (LRS) Experiment On-Board the SELENE Spacecraft
    Earth Planets Space, 52, 629–637, 2000 Lunar Radar Sounder (LRS) experiment on-board the SELENE spacecraft Takayuki Ono and Hiroshi Oya Department of Astronomy and Geophysics, Tohoku University, Sendai 980-8578, Japan (Received March 23, 2000; Revised August 11, 2000; Accepted September 1, 2000) The Lunar Radar Sounder (LRS) experiment on-board the SELENE (SELenological and ENngineering Explorer) spacecraft has been planned for observation of the subsurface structure of the Moon, using HF radar operating in the frequency range around 5 MHz. The fundamental technique of the instrumentation of LRS is based on the plasma waves and sounder experiments which have been established through the observations of the earth’s magnetosphere, plasmasphere and ionosphere by using EXOS-B (Jikiken), EXOS-C (Ohzora) and EXOS-D (Akebono) satellites; and the plasma sounder for observations of the Martian ionosphere as well as surface land shape are installed on the Planet-B (Nozomi) spacecraft which will arrive at Mars in 2003. For the exploration of lunar subsurface structures applying the developed sounder technique, discrimination of weak subsurface echo signals from intense surface echoes is important; to solve this problem, a frequency modulation technique applied to the sounder RF pulse has been introduced to improve the resolution of range measurements. By using digital signal processing techniques for the generation of the sounder RF waveform and on-board data analyses, it becomes possible to improve the S/N ratio and resolution for the subsurface sounding of the Moon. The instrumental and theoretical studies for developing the LRS system for subsurface sounding of the Moon have shown that the LRS observations on-board the SELENE spacecraft will give detailed information about the subsurface structures within a depth of 5 km from the lunar surface, with a range resolution of less than 75 m for a region with a horizontal scale of several tens of km.
    [Show full text]
  • Mars Express
    sp1240cover 7/7/04 4:17 PM Page 1 SP-1240 SP-1240 M ARS E XPRESS The Scientific Payload MARS EXPRESS The Scientific Payload Contact: ESA Publications Division c/o ESTEC, PO Box 299, 2200 AG Noordwijk, The Netherlands Tel. (31) 71 565 3400 - Fax (31) 71 565 5433 AAsec1.qxd 7/8/04 3:52 PM Page 1 SP-1240 August 2004 MARS EXPRESS The Scientific Payload AAsec1.qxd 7/8/04 3:52 PM Page ii SP-1240 ‘Mars Express: A European Mission to the Red Planet’ ISBN 92-9092-556-6 ISSN 0379-6566 Edited by Andrew Wilson ESA Publications Division Scientific Agustin Chicarro Coordination ESA Research and Scientific Support Department, ESTEC Published by ESA Publications Division ESTEC, Noordwijk, The Netherlands Price €50 Copyright © 2004 European Space Agency ii AAsec1.qxd 7/8/04 3:52 PM Page iii Contents Foreword v Overview The Mars Express Mission: An Overview 3 A. Chicarro, P. Martin & R. Trautner Scientific Instruments HRSC: the High Resolution Stereo Camera of Mars Express 17 G. Neukum, R. Jaumann and the HRSC Co-Investigator and Experiment Team OMEGA: Observatoire pour la Minéralogie, l’Eau, 37 les Glaces et l’Activité J-P. Bibring, A. Soufflot, M. Berthé et al. MARSIS: Mars Advanced Radar for Subsurface 51 and Ionosphere Sounding G. Picardi, D. Biccari, R. Seu et al. PFS: the Planetary Fourier Spectrometer for Mars Express 71 V. Formisano, D. Grassi, R. Orfei et al. SPICAM: Studying the Global Structure and 95 Composition of the Martian Atmosphere J.-L. Bertaux, D. Fonteyn, O. Korablev et al.
    [Show full text]
  • Electromagnetic Compatibility (EMC) Evaluation of the SELENE Spacecraft for the Lunar Radar Sounder (LRS) Observations
    Earth Planets Space, 60, 333–340, 2008 Electromagnetic compatibility (EMC) evaluation of the SELENE spacecraft for the lunar radar sounder (LRS) observations A. Kumamoto1,T.Ono1, Y. Kasahara2, Y. Goto2, Y. Iijima3, and S. Nakazawa4 1Graduate School of Science, Tohoku University, 6-3, Aoba, Aramaki, Aoba, Sendai 980-8578, Japan 2Graduate School of Natural Science and Technology, Kanazawa University, 2-40-20, Kakuma-machi, Kanazawa 920-1192, Japan 3Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, 3-1-1, Yoshinodai, Sagamihara 229-8510, Japan 4Tsukuba Space Center, Japan Aerospace Exploration Agency, 2-1-1, Sengen, Tsukuba 305-8505, Japan (Received March 16, 2007; Revised July 12, 2007; Accepted August 3, 2007; Online published April 9, 2008) In order to achieve the lunar subsurface sounding and planetary radio wave observations by the Lunar Radar Sounder (LRS) onboard the SELENE spacecraft, strict electromagnetic compatibility (EMC) requirements were applied for all instruments and the whole system of the spacecraft. In order to detect the lunar subsurface echoes from a depth of 5 km, the radiated emission (RE) limit was determined to be −10 dBμV/m and the common- mode (CM) current limit to be 20 dBμA. The EMC performance of the spacecraft was finally evaluated in the system EMC test held from Oct. 20 to Oct. 22, 2005. There is no broadband noise but some narrowband noises at a level above the CM-current limit in a frequency range from 4 to 6 MHz, in which radar soundings are operated. Based on the noise spectrum within 4–6 MHz, the noise level of FMCW radar sounder is estimated to be 14 dB lower than the CM-current limit.
    [Show full text]
  • Successes and Failures of Recent Mars Exploration
    Successes and Failures of Recent Mars Exploration Paul Withers [email protected] Boston University’s Center for Space Physics 2004.02.13 Bill Waller’s undergrad seminar class at Tufts University Aims of this talk • Describe the past decade of Mars exploration • Describe how half of attempted missions failed • Describe how NASA responded to failures in short and long term • Discuss lessons learned • Not an overview of Mars science Sequence of Missions • Mars Observer (1992) failure • Mars 96 (1996) [Russia] failure • Mars Pathfinder (1996) success • Mars Global Surveyor (1996) success • Nozomi (1998) [Japan] failure • Mars Climate Orbiter (1998) failure • Mars Polar Lander (1999) failure • Deep Space 2 (1999) (2 small probes) failure (x2) • 2001 Mars Odyssey (2001) success • Mars Express (2003) [ESA] success (?) • Beagle 2 (2003) [ESA/UK] failure • Mars Exploration Rovers Spirit and Opportunity (2003) success (x2) (?) • 12 years, 14 spacecraft, 8 failures, 3 successes, 3 probable successes Mars Observer (1992) Scientific Aims of Mars Observer • Global topo and gravity map • Measure magnetic field • Elemental makeup of surface • 2m-pixel images of surface • Mineralogical map of surface • Study atmospheric circulation • $980 mission, first US mission to Mars since Viking in 1976. Failure of Mars Observer • Plan: Pressurize fuel tank a few days before Mars Orbit Insertion • Plan: Turn transmitter off during pressurization to protect its components from shock, turn on again after pressurization complete • Reality: No further transmissions received after start of pressurization, complete loss of mission. • Failure Analysis: A fuel line ruptured during pressurization and the corrosive fuel disabled the spacecraft. Some parts were designed assuming pressurization after launch, not many months after launch.
    [Show full text]