(Maven) Mission

https://ntrs.nasa.gov/search.jsp?R=20160000802 2019-08-31T04:44:51+00:00Z

TRANSFER TRAJECTORY DESIGN FOR THE MARS ATMOSPHERE AND VOLATILE EVOLUTION (MAVEN) MISSION

David Folta*, Stuart Demcak#, Brian Young#, Kevin Berry$

The Mars Atmosphere and Volatile EvolutioN (MAVEN) mission will determine the history of the loss of volatiles from the Martian atmosphere from a highly inclined elliptical orbit. MAVEN will launch

from Cape Canav~alAir Force Station on an Atlas-V 401 during an extended 36-day launch period opening November 18, 2013. The .MAVEN Navigation and Mission Design team performed a Monte Carlo analysis of the Type-II transfer to characterize; dispersions of the arrival B-Plane, trajectory correction maneuvers (TCMs), and the probability of Mars impact. This paper presents detailed analysis of critical MOI event coverage, maneuver constraints, fl.V -99 budgets, and Planetary Protection requirements.

INTRODUCTION The Mars Atmosphere and Volatile EvolutioN (MAVEN) mission will determine the history of the loss of volatiles from the Martian atmosphere to space and in so doing will determine the 1 2 3 impact of this process on the climate, the habitability, and the presence of liquid water. • • MAVEN will achieve this by providing a comprehensive picture of the present state of the upper atmosphere and ionosphere of Mars and the processes controlling these regions from a highly inclined elliptical orbit.

MAVEN will launch from Cape Canaveral Air Force Station (CCAS) on an Atlas-V 401 during a unique extended 36-day launch period which opens November 18, 2013. The worst-case combination of injection energy (C3) and outbound declination provides a substantial mass margin for the launch capability. Upon arrival at Mars on September 22nd, 2014 (September 28tt\ for a nominal launch window close), MAVEN will perform a designed pitched-over capture maneuver with a nominal thrust of 1321N, imparting a delta-V (tl.V) of approximately 1233 m/sec over 36 minutes to achieve a 35-hr capture orbit at 75° inclination with a post-capture periapsis radius of 3779 km. Subsequent transition maneuvers will reduce the period to 4.5-hrs with the periapsis altitude within a required atmospheric density corridor of0.05 kglkm3 to 0.15 3 kglkm • A northern approach with a 5:45 pm local arrival time provides Earth visibility during the insertion burn.

"' Flight Dynamics Engineer, NASA Goddard Space Flight Center, Building 11, RoomS 116, Greenbelt, Maryland 20771. Senior Member AIAA, david.c.folta@nasa.gov #Jet Propulsion Laboratory, California Institute of Technology, M.S. 264-282, 4800 Oak Grove Dr., Pasadena, CA 91109, 818.393.7961, [email protected], and [email protected] s Flight Dynamics Engineer, NASA Goddard Space Flight Center, Building 1.1, Room S 116, Greenbelt, _Maryland 20771., [email protected]

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is is it it and of solar storms, all of which c·an affect the behavior of the top of the atmosphere. Figure 1 shows the different atmospheric loss and energy processes that MAVEN will measure. Neutral processes are shown in blue, ion and plasma processes in red, and solar energetic inputs are shown in the upper left. Spacecraft Overview The MAYEN spacecraft, shown in Figure 2, is the latest in a series of Lockheed Martin Mars orbiters to be developed for NASA (past orbiters include the Mars Global Surveyor, Mars Odyssey, and Mars Reconnaissance Orbiter (MR0)).5 Spacecraft features include redundant star· trackers and Inertial Measurement Units (IMU); two 50·hour nickel hydrogen batteries; two fixed solar arrays; low·gain and high-gain antennas; a mono-propellant system; redundant Command & Data Handling system; and a fault·tolerant Mars Orbit Insertion (Mon design. In addition, it is a 3-axis stabilized sun·pointing spacecraft, with a fixed high gain antenna. The spacecraft accommodates eight instruments (see Figure 3) that are segregated into three distinct packages: a Particles & Fields (P&F) package being developed by UC-Berkeley/Space Sciences Laboratory; a Remote Sensing Package being developed by CU-LASP; and the Neutral Gas and Ion Mass Spectrometer (NGIMS) being developed by GSFC.

Figure 2. MAVEN Spacecraft

MAVEN TRANSFER TRAJECTORY DESIGN MAVEN will launch from Cape Canaveral Air Force Station (CCAS) during a 36-day launch period (a 20·day nominal period with 16·days extended) opening November 18, 2013 on an ATLAS-V 401; The worst-case combination of injection energy and launch declination results in an allowable launch mass margin for the proposed 2354 kg current best estimate wet mass. Upon arrival at Mars on September 22, 2014 (September 28, for a Dec 7, 2013 nominal launch period close), MAVEN will insert into a capture orbit with a 35~hourpenod. Figure 3 shows the transfer trajectory and the dates of launch and arrival at Mars including the locations of all the planned TCMs. As with most planetary launches, there is a trade between the launch energy (C3), launch declination, and the arrivcll V-Infinity as these parameters vary over the launch period and they can become the driver for the mission design and propulsion system selection.

3 For MAVEN, a change in arrival date by a week can result in an increase in the arrival V infinity without a significant change to C3. The increased V- infinity yields an increase in / MOl fl.V of - 50 m/s. Since the propellant tank is full, a late arrival scenario is highly unfavorable as there is no additional propellant margin. Figure 4 shows contours of the C3 and V-Infinity for the desired launch Mars a period. One can see in Figure 4a that the C3 Arrival over the launch departure dates are relative 9/22/14 flat and decrease over the period by 2.6 2 2 km /s • The V-Infmity in Figure 4b however, has only a short duration where it remains flat near the minimum of 3.17 km!s. With a Figure 3 MAVEN Type - II Ballistic Transfer decreasing C3 over the launch period, the MOl fl. V detennined from V -infmity determines the close of the launch period. The launch declination remains under 28 degrees over the nominal launch period and thus does not pose a concern for reduced mass capability. Table 1 provides launch period information for the MAVEN mission.

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Table 1: Analytical Launch Period Parameters

Launch Period Open. Mid Close C3(km.Zti-) 1207 1030 9.40 Declination (de g) 13.38 18.84 26.93 Right A~nsion{deg) 198.26 200.58 200.88 Arrival date 9/22/2014 9/24/2014 9/28/2014 Arrival V -Infinity 317 315 3.17

4 Selection ofB-Piane Components The selection of the target B-Plane begins· with the completion of the determination of the ballistic type-II transfer. We initiated simulations using a full ephemeris and high fidelity environmental models to define transfer trajectories that propagated to the Mars periapsis. The B plane components as defined in Figure 5 are computed at the epoch of the periapsis event. B plane components are defined similarly to past Mars mission design references. The coordinates used for the B-Planes in this paper are based on the Mars Mean Equator IAU definition, with k being the Mars' North Pole. Note that the B.R negative direction is 'upward' and the B-angle increases in a counterclockwise direction.

The selection of the targeted B-Plane components is a result of several considerations. It must meet the planetary protection goals of less than 1 e-4 probability [reference 9] and meet the operational goal of a first TCM of 4 m/s minimum. This minimum AV is chosen so that the designed propulsion system can reach a steady state condition to successfully test the orbit insertion thrusters at an early portion in the transfer timeline. The current schedule has the first maneuver, TCM-1, occurring 15-days after injection. The chosen schedule permits ·time for navigation and other spacecraft operations to be completed.

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Transfer Injection Position State Generation To obtain the initial states for our process, a simplified B-plane determination process was used and iterated with KSC and the Launch Vehicle Provider, ULA. Using high fidelity simulations with environmental models from all past Mars missions and estimates of the initial launch conditions, we targeted to the desired orbit insertion conditions. Starting with this information and an estimated TIP error matrix based on preliminary information exchanged with ULA, the direction of the maximum and minimum TCM -1 A.V vectors can be computed for a preliminary estimate of the target B-Plane components that meets the planetary protection and TCM-1 AV requirement. From this iterated analysis, a selected B-Plane aimpoint was chosen with components ofB.T = 16100 krn, and B.R = -19300 km.

This aimpoint applies to the optimal condition of the daily launch window for the full launch period. For the first and second Configuration, Perfornla.nce and Weight Status Report (CPWSR) delivery the B-Plane targets were held constant across the nominal launch period. Initial targeting simulations gave the results shown in Table 2 over the entire launch period. The table presents the

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' TCM-1 AV Statistics With the B-Plane distribution statistical analysis completed, we determined the TCM-1 budget for the transfer trajectory. For each of the cases provided above, the distribution of the TCM-1 ~V performed at injection plus 15 days is shown. As can be seen the variation in the TCM-1 ~V magnitude can be quite large, ranging from approximately 2 m/s to over 15 m/s depending on the launch date and the time of day of launch. Figures 18 through 21 show the TCM-1 ~V magnitude (units ofkmls) distribution for each launch condition corresponding to the above B-plane distribution and P[l]. Using the tl.V magnitude and MATLAB statistical functions (e.g. percentile, mean, median), Table 3 provides the statistical analysis of these plots and the 3- 1 sigma and tl.V-99 for the nominal launch period. The extended launch period date of Dec 15 h indicates a tl.V magnitude that approaches 50 m/s. While the tl.V magnitude is larger than the allowable TCM-1 ~V budget of 20 m/s, it is still within family when considering the total tl.V budget and the desire to launch during the 2013 cycle. The epoch ofTCM-1 can also be adjusted to vary the magnitude of the TCM -1 tl.V in order to maintain a minimum 4 .m/s requirement. . """111bl'lua1hrTCM1DVo1 151tn

Figure 18. TCM-1 AV s for Launch Open, Nov 18th 2013, with 2-hr window

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Figure 19. TCM-1 AV s for Launch Mid, Nov 27th 2013, with 2-hr window

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200 400 Ta.l-1 OVmagniOirle ot 15 days Figure 21 TCM-1 AV s for Launch Extended, Dec 15th 2013, with 2-hr window

12 Table 3. TCM-1 Statistical A.V Information Max Min Mean Std 3-sigma DV-99 Launch date and window (m/s) (m/s) (m/s) (m/s) (m/s) (m/s) Nov 18 Minuslhr 9.6 1.2 4.9 1.2 8.6 . 7.9 Nov 18 Optimal 12.8 1.7 5.5 1.5 10.1 9.6 Nov 18 Plu!: lhr 12.9 2.4 6.6 1.8 11.9 11.2 Nov 27 Minus lhr 9.9 2.1 5.4 1.2 9.0 8.6 Nov 27 Opt1mal 13.0 2.3 6.4 1.7 11.4 10.5 Nov 27 Plus lhr 15.1 2.7 8.2 2.0 14.1 13.0 D~c07 Minus lhr 11.1 1.8 5.7 1.5 10.3 9.7 Dec 07 Optimal 15.5 3.8 8.9 1.9 14.6 13.4 Dec 07 Plus lhr 20.3 6.8 13.1 2.3 20.0 .. 18.6

ADDITIONAL DESIGN CONSIDERATIONS

Modeling and Optimization

The .environmental models used for the analysis presented above are representative of all previous Mars missions and the MAVEN Mission Design and Navigation team has thoroughly verified consistent and accurate trajectory designs using both the AGI Astrogator V9.2 and JPL's MONTE software. As part of the ongoing analysis the team is well aware that optimizing a

combination ofTCM-1 1~.Vat 15-days after launch with the TCM-2 !:N performed 90 days after launch would benefit the overall TCM budget as well as permit more operatiqnal options. The TCM-1 in this optimization process could be held to the required 4 m/s magnitude.

Orbit Plan Angle

As seenin several figures, the slope (angle wrt the B.T direction) of the B-Plane distribution ranges from~11-deg to --45-deg over the launch period. This angle plays an important function in the magnitude of the TCM-1 ll.Vs. The importance of the distribution is in the TCM ll.Vs to correct the trajectory from the biased aimpoint back to the required insertion conditions. The ll Vs are minimal in the B.T direction as that direction is a heliocentric orbit period correction. The llV to change the B.R direction is larger as it is associated with a heliocentric inclination or arrival declination change. Also the location of the TCM-1 maneuver is not optimal wrt to inclination changes nor represents an optimal broken plane maneuver. With the opening launch date arrival conditions, ihe heliocentric inclination is - 2-deg and increases nearly 1-deg towards the launch closure date. The Mars incoming declination varies from -20-deg at opening to -33-deg at closure.

MOl constraints

As part of the various rules and goals with respect to observation of critical events, the timing .of the MOl and the targeted Mars arrival epoch was controlled such that two independent DSN sites could maintain coverage of the complete MOl duration. This is a straight forward targeting strategy in that the arrival epoch of Mars periapsis is targeted in the overall design process. .This arrival time is dependent upon the dual coverage of both Canberra and Goldstone DSN sites for MOl and is centered at 02:00 hrs. Since the MOl maneuver is approximately 36 minutes in duration, even with fault tolerant measures in place, this dual coverage permits either site coverage throughout the maneuver. Other launch period dates are similar since the arrival time is

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