火星探测器近心点制动与轨道保持优化设计
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摘要
随着新世纪火星探测热潮的到来,火星探测器近心点制动与轨道保持问题成为了研究热点。本文以工程项目“深空探测航天器自主轨道控制优化计算”为背景,研究火星探测器近火星点制动策略和轨道保持策略问题,本文的创新点在于,第一,将虚拟卫星方法用于火星探测器近心点制动中,解决了由双曲线进入轨道制动并精确进入工作轨道的问题;第二,推导小推力轨道保持算法并用于火星探测器轨道保持任务中,解决了有摄动情况下火星探测器轨道长时间保持问题。
本论文以火星探测器为研究对象,根据不同任务的需要,建立了相应的坐标系统,并给出了考虑多种摄动因素在内的火星探测器动力学模型,摄动源包括火星10阶非球形摄动,太阳引力摄动和地球引力摄动,该模型的精确性较高,可以进行长时间轨道积分运算。
本论文对火星探测器近火星点制动问题进行了分析,推导了固定推力策略和最优推力策略两种制动方法,两种方法均能较好地完成火星探测器制动任务,但精度有所不同。其中,最优推力策略采用虚拟卫星方法,结果显示,该方法能够用于双曲线轨道向椭圆轨道的转移任务。
本论文以考虑摄动因素的火星探测器动力学模型为基础,精确分析了火星探测器长期运行的轨道要素变化情况。推导了小推力轨道保持算法,仿真结果显示,该方法可以实现发动机开机次数少,节约燃料等工程指标。
本文所得到的研究成果可以作为后续研究的参考。
With the arrival of the upsurge of Mars Exploration in the new century, it is going to become hot topic that Mars probe brakes near the Mars and keeps its orbit in a long time. In this paper, with“Deep space probe autonomous orbit control optimization”as the background, we discussed the problems of braking near the Mars and orbit keeping for Mars probe. There were two innovations which are, firstly, using the virtual satellite method in near Mars braking and secondly, deriving low-thrust orbit keeping algorism.
In the paper, according to the needs of different tasks, appropriate coordinate systems were established and a dynamic model considering various perturbation factors was given. The perturbation includes Mars Non-spherical gravitational perturbation, sun and earth gravitational perturbation. The high accuracy dynamic model will be used in the orbital integral.
This paper analyzed the near Mars braking problem and derived, respectively, fixed-thrust and optimal-thrust braking algorism both of which could accomplish the near Mars braking mission well, however, the results were different in accuracy. The virtual satellite method was used in optimal-thrust algorism. It’s proved that this method could be used in the transfer between hyperbolic orbit and elliptical one.
In the paper, according to the high accuracy dynamic model, it was analyzed that the orbit elements of the Mars probe would change in the long term. A low-thrust orbit keeping algorism was derived. From the result we could see that this algorism would lower the fuel expend and the number of starting engine.
The results obtained in this dissertation can provide theoretic reference to the further research.
本论文以火星探测器为研究对象,根据不同任务的需要,建立了相应的坐标系统,并给出了考虑多种摄动因素在内的火星探测器动力学模型,摄动源包括火星10阶非球形摄动,太阳引力摄动和地球引力摄动,该模型的精确性较高,可以进行长时间轨道积分运算。
本论文对火星探测器近火星点制动问题进行了分析,推导了固定推力策略和最优推力策略两种制动方法,两种方法均能较好地完成火星探测器制动任务,但精度有所不同。其中,最优推力策略采用虚拟卫星方法,结果显示,该方法能够用于双曲线轨道向椭圆轨道的转移任务。
本论文以考虑摄动因素的火星探测器动力学模型为基础,精确分析了火星探测器长期运行的轨道要素变化情况。推导了小推力轨道保持算法,仿真结果显示,该方法可以实现发动机开机次数少,节约燃料等工程指标。
本文所得到的研究成果可以作为后续研究的参考。
With the arrival of the upsurge of Mars Exploration in the new century, it is going to become hot topic that Mars probe brakes near the Mars and keeps its orbit in a long time. In this paper, with“Deep space probe autonomous orbit control optimization”as the background, we discussed the problems of braking near the Mars and orbit keeping for Mars probe. There were two innovations which are, firstly, using the virtual satellite method in near Mars braking and secondly, deriving low-thrust orbit keeping algorism.
In the paper, according to the needs of different tasks, appropriate coordinate systems were established and a dynamic model considering various perturbation factors was given. The perturbation includes Mars Non-spherical gravitational perturbation, sun and earth gravitational perturbation. The high accuracy dynamic model will be used in the orbital integral.
This paper analyzed the near Mars braking problem and derived, respectively, fixed-thrust and optimal-thrust braking algorism both of which could accomplish the near Mars braking mission well, however, the results were different in accuracy. The virtual satellite method was used in optimal-thrust algorism. It’s proved that this method could be used in the transfer between hyperbolic orbit and elliptical one.
In the paper, according to the high accuracy dynamic model, it was analyzed that the orbit elements of the Mars probe would change in the long term. A low-thrust orbit keeping algorism was derived. From the result we could see that this algorism would lower the fuel expend and the number of starting engine.
The results obtained in this dissertation can provide theoretic reference to the further research.
引文
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2叶培建,邓湘金,彭兢.国外深空探测态势特点与启示(上)[J].航天器环境工程,2008,25(5):401-416
3叶培建,邓湘金,彭兢.国外深空探测态势特点与启示(下)[J].航天器环境工程,2008,25(6):501-512
4尹大伟,文援兰,刘峰,廖瑛.火星探测器飞行轨道设计[J].飞行力学,2009,27(5):40-43
5李爽,彭玉明,陆宇平.火星EDL导航、制导与控制技术综述与展望[J].宇航学报,2010,31(3): 621-627
6 G.Scott Hubbard.The exploration of Mars,historical context & current results[J]. 42nd AIAA Aerospace Sciences Meeting and Exhibit 5 - 8 January 2004, Reno,Nevada:1-10.
7 Adams,Alan,Sumrall,Phil.Overview of Mars transportation options and issues[J].Space Programs and Technologies Conference,Huntsville,AL,Sept 25-27,1990:1-21
8 Manuel I, Marc R. 21st century early mission concepts for Mars delivery and earth return[J].AIAA/AAS Astrodynamics Conference,Portland,OR,Aug 20-22, 1990, Technical Papers.Part 1 (A90-52957 24-13).Washington,DC,American Institute of Aeronautics and Astronautics,1990:246-258.
9陈昌亚,方宝东,曹志宇,江世臣,侯建文.YH-1火星探测器设计及研制进展[J].上海航天,2009,(3):21-25
10 J?rg Fischer,Michel Denis,Alan Moorhause,Zeina Mounzer.Planetary Orbit Insertion - A First Success for Europe with ESAs Mars express[J].SpaceOps 2006 Conference,Rome,Italy,June 19-23,2006:1-26
11 Howard D,Curtis.轨道力学.科学出版社,2009:5
12佘明生.地球观测卫星的轨道捕获和轨道保持[J].中国空间科学技术,1982,(3) :47-53
13刘林,汤靖师.火星轨道器运动的轨道变化特征[J].宇航学报,2008,29(2):71-76
14 Bonnard,B.Geometric optimal control and transfer between elliptic Keplerian orbits[J].43rd IEEE Conference on Decision and Control,2004,2(1):1364
15 Rusnak I . Optimal guidance laws with uncertain time-of-flight[J]. IEEE Transactions on Aerospace and Electronic Systems, 2000,36(2):721– 725
16 Carpenter B,Jackson B.Stochastic optimization of spacecraft rendezvous trajectories.IEEE Aerospace Conference,2003,8 (1):3731– 3738
17 Yuri Ulybyshev . Continuous Thrust Orbit Transfer Optimization Using Large-Scale Linear Programming [J].Journal of Guidance,Control,and Dynamics. 2007,30(2):427-436.
18 Brian Roger Jamison,Victoria Coverstone.Analytical Study of the Primer Vector and Orbit Transfer Switching Function [J].Journal of Guidance,Control,andDynamics. 2010,33(1):235-245
19 Jayaraman,T.S.Alam,M.Application of the Conjugate Gradient Method to a Problem on Minimum Time Orbit Transfer [J].IEEE Transactions on Aerospace and Electronic Systems,1975,11(3):406– 412
20 Yumin Chen , Donglong Sheu . Parametric Optimization Analysis for Minimum-Fuel Low-Thrust Coplanar Orbit Transfer[J].Journal of Guidance,Control,and Dynamics 2006,29 (6 ):1446-1451
21刘鲁华.航天器自主交会制导与控制方法研究[D].国防科学技术大学,2007
22李亮.航天器轨道转移与交会最优控制研究[D].西北工业大学,2005
23王小军,吴德隆,余梦伦.最少燃料消耗的固定推力共面轨道变轨研究[J].宇航学报,1995,16(4).9-16
24岳新成,杨莹,耿志勇.有限推力能量、燃料最优轨道转移控制[J].南京航空航天大学学报,2009,41(6):715-719
25梁新刚,杨涤.应用非线性规划求解异面最优轨道转移问题[J].宇航学报,2006,27(3): 365-370
26梁新刚,杨涤.有限推力下时间最优轨道转移[J].航天控制,2007,25(1): 46-51
27刘峰.有限推力轨道转移优化方法与应用研究[D].国防科学技术大学,2009.
28丁濛，童若锋，董金祥．大范围轨道机动的燃料消耗优化方法[J].航天控制,2008,26(6):47-53
29李桢,李海阳,程文科.载人火星任务气动捕获段轨道初步设计[J].国防科技大学学报,2010,32(3):42-47
30张巍,方群,袁建平.最小燃料消耗的有限推力轨道转移优化设计[J].西北工业大学学报,2008,26(5):616-620
31张亚锋,和兴锁.基于Gauss伪谱法的有限推力轨道转移优化[J].航天控制,2010,28(3):38-41
32涂良辉,袁建平,罗建军.基于伪光谱方法的有限推力轨道转移优化设计[J].宇航学报,2008,29(4):1190-1193
33荆武兴,吴瑶华.卫星轨道圆化的有限推力点火控制策略[J].宇航学报,1997,18(4):1-6
34荆武兴,吴瑶华,杨涤.基于交会概念的最省燃料共面有限推力轨道转移方法[J].哈尔滨工业大学学报,1997,29(4):132-135
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