火星环绕器火卫一抵近探测拓展任务轨道设计与分析

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doi:10.15982/j.issn.2096-9287.2023.20220080

郑惠欣^{1, 2,},
谢攀^{1, 2,},
李海洋^{1, 2},
朱新波^{1, 2}

1.
上海卫星工程研究所，上海 201109
2.
上海市深空探测技术重点实验室，上海 201109

基金项目:十四五民用航天技术预先研究项目-XX探测顶层设计与关键技术研究（D050201）；上海市青年科技英才扬帆计划（21YF1446100）；国家自然科学基金青年基金（12102265）

详细信息

作者简介:
（1995− ），女，工程师。主要研究方向：航天器轨迹优化。通讯地址：上海市闵行区元江路3666号上海卫星工程研究所（201109）电话：（021）24230000−6625E-mail：zhenghuixin95@163.com
（1984− ），男，高级工程师。主要研究方向：航天器总体设计。通讯地址：上海市闵行区元江路3666号上海卫星工程研究所（201109）电话：（021）24230423E-mail：xiepansh@163.com

●　Under the condition that the remaining fuel of Tianwen-1 Mars orbiter was considerably limited and the Orbiter could not be directly transferred to the orbit of Phobos, this paper utilized Mars perturbation force in adjusting the argument of perigee to make the orbit of the orbiter intersect with the orbit of Phobos. ●　The intersecting frequency between the orbit of Tianwen-1 Mars orbiter and Phobos is related to the value of semi-major axis and eccentricity. The intersecting frequency can be maximized by designing appropriate orbital parameters. ●　In order to complete the close approach detection of Phobos, the Orbiter has to maneuver from the remote sensing orbit to the extended mission orbit. The Mars aero-braking is adopted as the orbital descent maneuver strategy, which can reduce fuel consumption by 80%. ●　By designing an appropriate phase adjustment orbit period, the phase adjustment velocity increment can be controlled to within 10m/s under the worst conditions of approach detection phase.
中图分类号:TP18

Orbit Design and Analysis of Phobos Close Approach Exploration Mission for Tianwen-1 Mars orbiter

ZHENG Huixin^{1, 2,},
XIE Pan^{1, 2,},
LI Haiyang^{1, 2},
ZHU Xinbo^{1, 2}

1.
Shanghai Institute of Satellite Engineering, Shanghai 201109, China
2.
Shanghai Key Laboratory of Deep Space Exploration Technology, Shanghai 201109, China

摘要:针对“天问一号”火星环绕器火卫一抵近探测拓展任务设想开展了任务轨道设计与分析，将主任务结束后的状态作为拓展任务的输入，对拓展任务轨道、变轨策略及燃料代价进行设计。通过分析得出，可利用火星摄动力调整近火点幅角使得环绕器轨道与火卫一轨道相交，且相交频率与半长轴和偏心率相关。为提高相交次数需进行降轨，进一步分析了利用火星大气辅助降轨以降低燃料消耗、提高轨道相交次数的可能性，最后通过调相机动的方式使环绕器完成火卫一抵近探测任务。仿真结果表明：所设计的拓展任务轨道及变轨策略的速度增量代价合理可行，可为后续火星环绕探测任务轨道设计提供参考。
- 火卫一抵近探测/
- 轨道设计/
- “天问一号”火星环绕器
Abstract:In this paper, the mission orbit design and analysis of a potential extended mission, Phobos close approach exploration, was carried out. The state at the end of the main mission was used as the input of the extended mission in this paper. Through analysis, it was concluded that Mars perturbation force could be used to adjust the argument of perigee, and the intersection frequency was related to the value of semi-major axis and eccentricity. Orbit descent maneuver should be performed to increase the number of intersections. As a result, the possibility of conducting aero-braking in order to reduce fuel consumption was analyzed. Finally, phase adjustment maneuver was calculated to complete the Phobos close approach exploration mission. The orbit design results and the velocity increment are given by simulation. The results of this paper can provide reference for orbit design of Tianwen-1 orbiter’s extended missions.
- Phobos close approach exploration/
- orbit design/
- Tianwen-1 Mars orbiter
Highlights

●　Under the condition that the remaining fuel of Tianwen-1 Mars orbiter was considerably limited and the Orbiter could not be directly transferred to the orbit of Phobos, this paper utilized Mars perturbation force in adjusting the argument of perigee to make the orbit of the orbiter intersect with the orbit of Phobos. ●　The intersecting frequency between the orbit of Tianwen-1 Mars orbiter and Phobos is related to the value of semi-major axis and eccentricity. The intersecting frequency can be maximized by designing appropriate orbital parameters. ●　In order to complete the close approach detection of Phobos, the Orbiter has to maneuver from the remote sensing orbit to the extended mission orbit. The Mars aero-braking is adopted as the orbital descent maneuver strategy, which can reduce fuel consumption by 80%. ●　By designing an appropriate phase adjustment orbit period, the phase adjustment velocity increment can be controlled to within 10m/s under the worst conditions of approach detection phase.

图 1天问一号火星环绕器示意图^[2]

Fig. 1Tianwen-1 Mars orbiter configuration diagram^[2]

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图 2改变速度矢量方向示意图

Fig. 2Diagram of direction change of velocity vector

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图 3近火点幅角平根在高精度模型和考虑J4摄动项下递推结果

Fig. 3Comparison of mean argument of periapsis recursion results under high-precision model and with J4 perturbation terms

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图 4环绕器遥感轨道升/降交点半径与火卫轨道半径

Fig. 4Remote sensing orbit ascending/ descending node radius and radius of Phobos orbit

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图 5远火点高度变化下环绕器升/降交点半径与火卫轨道半径

Fig. 5Mars orbiter ascending/ descending node radius and radius of the Phobos orbit under the change of apogee altitude

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图 7常规燃料机动降轨和大气辅助降轨方式的速度增量对比

Fig. 7Comparison of velocity increments between conventional fuel maneuver and Mars aerobraking orbital descent modes

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图 8抵近探测最恶劣相对相位条件示意图

Fig. 8Diagram of worst relative phase conditions for Phobos close approach exploration

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图 9同一火卫运行圈数对应 < 1 km/s速度增量曲线

Fig. 9Same Phobos cycle number corresponding to velocity increment less than1 km/s

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图 6远火点高度变化下环绕器轨道与火卫轨道相交次数变化

Fig. 6Number of intersecting times between two orbits changing with apogee altitude

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表 1各探测器的大气辅助降轨效果

Table 1Aero-braking results of Probes

任务名称	大气辅助降轨前远星点高度/km	大气辅助降轨后远星点高度/km	节省燃料/kg	大气辅助降轨时长
Magellan	8 450	540	490	约70 d
MGS	54 200	430	330	约300 d
Odyssey	26 200	540	320	约76 d
MRO	44　000	500	580	约6个月
MAVEN	6 200	4 500	100	约50 d
ExoMars	33 000	1 000	300	约8个月

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表 2调相速度增量数据表

Table 2Velocity increment data of phase adjustment

速度增量/（m·s^-1）	M= 1.5	M= 2.5	M= 3.5	M= 4.5	M= 5.5	M= 6.5	M= 7.5	M= 8.5	M= 9.5	M= 10.5
N= 4	886.50	102.64	453.90	642.17	762.06	846.19	909.00	957.99	997.46	1030.05
N= 5	1 486.94	214.42	225.15	458.69	606.74	710.31	787.49	847.60	895.97	935.87
N= 6	2 090.17	517.29	9.33	286.58	461.54	583.58	674.35	744.94	801.68	848.45
N= 7	2 713.29	811.61	197.69	122.46	323.55	463.42	567.25	647.89	712.63	765.94
N= 8	3 375.24	1 101.08	398.48	35.750	190.98	348.25	464.76	555.12	627.59	687.21
N= 9	4 103.44	1 388.38	594.80	189.48	62.64	237.00	365.93	465.77	545.75	611.51
N= 10	4 949.3	1 675.71	787.94	339.71	62.34	128.91	270.06	379.20	466.55	538.30
N= 11	6 052.94	1 964.97	978.88	487.22	184.59	23.430	176.65	294.96	389.54	467.17
N= 12	8 316.15	2 257.98	1 168.44	632.59	304.62	79.880	85.310	212.69	314.41	397.82
N= 13	8 652.11	2 556.62	1 357.31	776.32	422.82	181.36	4.2600	132.11	240.88	330.01
N= 14	8 966.79	2 862.92	1 546.11	918.81	539.51	281.30	92.310	52.990	168.76	263.54
N= 15	9 263.22	3 179.21	1 735.37	1 0 0.41	654.97	379.93	179.06	24.860	97.870	198.26
N= 16	9 543.78	3 508.35	1 925.64	1 201.41	769.43	477.44	264.67	101.59	28.060	134.02
N= 17	9 810.42	3 854.00	2 117.43	1 342.09	883.09	574.00	349.30	177.34	40.790	70.71
N= 18	10 064.71	4 221.13	2 311.26	1 482.7	996.13	669.77	433.07	252.22	108.78	8.24
N= 19	10 307.97	4 616.95	2 507.66	1 623.48	1 108.71	764.86	516.09	326.33	176.01	53.470
N= 20	10 541.30	5 052.75	2 707.22	1 764.64	1 220.97	859.40	598.47	399.77	242.55	114.51
N= 21	10 765.65	5 548.5	2 910.56	1 906.4	1 333.06	953.48	680.28	472.60	308.47	174.94
N= 22	10 981.82	6 146.91	3 118.39	2 048.97	1 445.09	1 047.2	761.61	544.89	373.84	234.81
N= 23	11 190.51	6 987.04	3 331.51	2 192.58	1 557.18	1 140.66	842.53	616.72	438.72	294.18

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表 3同一火卫运行圈数筛选对应的最小速度增量

Table 3The minimum velocity increment corresponding to the same number of Phobos cycle

参数	M= 1.5	M= 2.5	M= 3.5	M= 4.5	M= 5.5	M= 6.5	M= 7.5	M= 8.5	M= 9.5	M= 10.5
最小速度增量/（m·s^-1）	886.50	102.64	9.33	35.75	62.34	23.43	4.26	24.85	28.06	8.24
探测器运行圈数N	N= 4	N= 4	N= 6	N= 8	N= 10	N= 11	N= 13	N= 15	N= 16	N= 18
调相轨道周期/min	141.1	294.3	268.5	257.4	251.3	272.1	265.0	260.0	273.3	268.2

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表 4环绕器与火卫一不同初始相位差下的最小速度增量

Table 4Minimum velocity increment at different initial phase differences between satellite and Phobos

参数	值
环绕器与火卫一初始相位差	30°	45°	90°	135°	180°
最小速度增量/（m·s^-1）	3.37	2.56	1.83	0.98	4.26
火卫一运行圈数	8.08	8.13	9.25	6.375	7.5
探测器运行圈数	14	14	16	11	13

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表 5拓展任务轨道机动速度增量

Table 5Maneuver velocity increment of additional tasks

机动动作	速度增量/（m·s^–1）
远火点机动，降低近火点高度至110 km	10.2
远火点机动，抬高近地点高度至260 km	13.4
近火点调相机动	9.33
合计	32.93

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[1]	吴伟仁,于登云. 深空探测发展与未来关键技术[J]. 深空探测学报(中英文),2014,1(1):5-17. WU W R,YU D Y. Development of deep space exploration and its future key technologies[J]. Journal of Deep Space Exploration,2014,1(1):5-17.
[2]	朱新波,谢攀,徐亮,等. “天问一号”火星环绕器总体设计综述[J]. 航天返回与遥感,2021,42(3):1-12. ZHU X B,XIE P,XU L,et al. Summary of the overall design of Mars orbiter of Tianwen-1[J]. Spacecraft Recovery and Remote Sensing,2021,42(3):1-12.
[3]	中国科学院月球与深空探测总体部. 月球与深空探测[M]. 广州: 广东科技出版社, 2014: 266-344.
[4]	朱新波,张玉花,徐亮,等. 火星环绕器行星际飞行设计与实现[J]. 上海航天(中英文),2022,39(S1):87-95. ZHU X B,ZHANG Y H,et al. Design and realization of interplanetary flight for Mars orbiter[J]. Aerospace Shanghai (Chinese and English),2022,39(S1):87-95.
[5]	耿言,陈刚. 天问一号完成既定科学探测任务[J]. 国防科技工业,2022(7):52-53. GEN Y,CHEN G. Tianwen-1 has completed its planned scientific exploration mission[J]. Defense Science,Technology and Industry,2022(7):52-53.
[6]	GIL P J S,Schwartz J. Simulations of quasi-satellite orbits around Phobos[J]. Journal of Guidance,Control,and Dynamics,2010,33(3):901-914.
[7]	吴晓杰,王悦,徐世杰. 考虑星历的火卫一邻近区域限制性多体问题建模与分析[J]. 动力学与控制学报,2021,19(2):1-7. WU X J,WANG Y,XU S J. Modeling and analysis of the restricted many-body problem in the vicinity of Phobos considering ephemeris[J]. Journal of Dynamics and Control,2021,19(2):1-7.
[8]	杨轩. 火星探测器精密定轨定位与火卫一低阶重力场研究 [D]. 武汉: 武汉大学, 2020. YANG X. Mars spacecraft precise orbit determination and Phobos gravity field recovery [D]. Wuhan: Wuhan University, 2020.
[9]	刘林, 汤靖师. 卫星轨道理论与应用[M]. 北京: 电子工业出版社, 2015.
[10]	韩波. 行星探测中的大气制动技术研究[D]. 杭州: 浙江大学, 2010. HAN B. Research on aerobraking of the planetary exploration [D]. Hangzhou: Zhejiang University, 2010.
[11]	LYONS D T,BEERER J G,ESPOSITO P,et al. Mars global surveyor:aerobraking mission overview[J]. Journal of Spacecraft and Rockets,1999,6(3):307-313.
[12]	SMITH J C,BELL J L. 2001 Mars Odyssey aerobraking[J]. Journal of Spacecraft and Rockets,2015,42(3):406-415.
[13]	LONG S M , YOU T H , HALSELL C A , et al. Mars reconnaissance orbiter aerobraking daily operations and collision avoidance [C]//The 20th International Symposium on Space Flight Dynamics. USA: [s. n. ]: 2007.
[14]	LEE Y, BENNA M, MAHAFFY P R. MAVEN NGIMS measurements of the Martian Ionosphere during the aerobraking campaign [C]//The 9th International Conference on Mars. Pasadena, USA: [s. n. ]: 2019.
[15]	DENIS M, SCHMITZ P, SANGIORGI S, et al. Thousand times through the atmosphere of Mars: aerobraking the ExoMars trace gas orbiter [C]//The 15th International Conference on Space Operations. France: [s. n. ], 2018.
[16]	艾远行. 火星气动捕获轨迹设计与制导方法研究[D]. 哈尔滨: 哈尔滨工业大学, 2017. AI Y X. Mars aerocapture trajectory design and Guidance [D]. Harbin: Harbin Institute of Technology, 2017.
[17]	DAVID A. Spencer and robert tolson. aerobraking cost and risk decisions[J]. Journal of Spacecraft and Rockets [J]. 2007, 44（6）: 1285-1293.

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注释:

●　Under the condition that the remaining fuel of Tianwen-1 Mars orbiter was considerably limited and the Orbiter could not be directly transferred to the orbit of Phobos, this paper utilized Mars perturbation force in adjusting the argument of perigee to make the orbit of the orbiter intersect with the orbit of Phobos.

●　The intersecting frequency between the orbit of Tianwen-1 Mars orbiter and Phobos is related to the value of semi-major axis and eccentricity. The intersecting frequency can be maximized by designing appropriate orbital parameters.

●　In order to complete the close approach detection of Phobos, the Orbiter has to maneuver from the remote sensing orbit to the extended mission orbit. The Mars aero-braking is adopted as the orbital descent maneuver strategy, which can reduce fuel consumption by 80%.

●　By designing an appropriate phase adjustment orbit period, the phase adjustment velocity increment can be controlled to within 10m/s under the worst conditions of approach detection phase.

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