低成本多小天体并行交会技术
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摘要
小天体资源开发方兴未艾,为降低开发风险和成本,需要发射无人探测器交会观测多个待选目标小天体。传统多目标探测方案存在无法多次交会、成本高,周期长等不足。提出的低成本多小天体并行交会技术,能够对多小天体探测任务进行解耦,实现基于微纳飞行器的低成本多目标并行交会勘查,从而降低探测成本,缩短探测周期。该技术结合行星借力与不变流形机制构建了低能量星际转移方案。然后引入扰动流形思想,使微纳飞行器能够实现与目标小天体的快速交会。进一步,提出了一种多目标小天体探测全局搜索方法,该方法基于在日地halo轨道上停泊的微纳飞行器集群,逐次确定小天体探测目标,并利用上述方法完成了多微纳飞行器与多小天体的交会。数值仿真结果表明,该方案能够大幅度降低转移过程的燃料消耗,并缩短转移时间。
To reduce the total cost and risk of asteroid exploration,it is necessary to select multi-objective to avoid the disadvantages such as single target,high-cost and long-period. In this paper,a multi-target transfer trajectory design method is proposed based on the cubesats with the cooperation of gravity flyby and invariant manifolds. Introduced by the perturbation invariant manifolds,the cubesat can rapidly transfer to the target and carry out a global launch chance searching for asgteroids based on the Sun-Earth Halo parking orbit and determine the next target. The results indicated that the proposed method is able to significantly reduce the fuel consumption of trajectory transfer as well as transfer time.
To reduce the total cost and risk of asteroid exploration,it is necessary to select multi-objective to avoid the disadvantages such as single target,high-cost and long-period. In this paper,a multi-target transfer trajectory design method is proposed based on the cubesats with the cooperation of gravity flyby and invariant manifolds. Introduced by the perturbation invariant manifolds,the cubesat can rapidly transfer to the target and carry out a global launch chance searching for asgteroids based on the Sun-Earth Halo parking orbit and determine the next target. The results indicated that the proposed method is able to significantly reduce the fuel consumption of trajectory transfer as well as transfer time.
引文
[1]李俊峰,曾祥远.不规则小行星引力场内的飞行动力学[J].力学进展,2017,47:429-451.LI J F,ZENG X Y.Flight dynamics in the gravitational fields of irregular asteroids[J].Advances In Mechanics,2017,47:429-451.
[2]李俊峰,曾祥远,张韵.小行星的奇特动力学1)[J].力学与实践,2016,38(6):603-611.LI J F,ZENG X Y,ZHANG Y.Unique dynamics of asteroids 1)[J].Mechanics in Engineering,2016,38(6):603-611.
[3]CANALIAS E,GOMEZ G,MARCOTE M,et al.Assessment of mission design includingutilization of libration points and weak stability boudaries[R].ESOC Contract18142/04/NL/MV,Final Report,2004.
[4]FARQUHAR R,MUHONEN D,RICHARDSON D.Mission design for a halo orbiter of the Earth[J].Journal of Spacecraft and Rockets,1977,14:170-177.
[5]张振江,崔祜涛,崔平远.基于三阶解析解的小行星平衡点附近halo轨道确定方法研究[J].宇航学报,2011,32(2):277-283.ZHANG Z J,CUI H T,CUI P Y.Research on third-order analytical solution determination of halo orbits around equilibrium point of asteroid[J].Journal of Astronautics,2011,32(2):277-283.
[6]FOLTA D,RICHON K.Libration orbit mission design at L2:A MAPand NGST perspective[C]//AIAA/AAS Astrodynamics Conference.Boston:AIAA/AAS,1998.
[7]于洋,宝音贺西.小天体附近的轨道动力学研究综述[J].深空探测学报,2014,1(2):93-104.YU Y,BAOYIN H X.Review of orbital dynamics in the vicinity of solar system small celestial bodies scientific vision for future missions[J].Journal of Deep Exploration,2014,1(2):93-104.
[8]吴伟仁,崔平远,乔栋,等.嫦娥二号日地拉格朗日L2点探测轨道设计与实施[J].中国科学:科学通报,2012,57(21):1987-1991.WU W R,CUI P Y,QIAO D,et al.Design and performance of exploring trajectory to Sun-Earth L2 point for Chang’E-2 mission[J].Chin Sci Bull,2012,57(21):1987-1991.
[9]曾祥远,李俊峰,刘向东.不规则小天体引力场内的广义甩摆轨道[J].深空探测学报,2016,3(1):29-33.ZENG X Y,LI J F,LIU X D.Generalized flyby trajectories over irregular-shaped small bodies[J].Journal of Deep Space Exploration,2016,3(1):29-33.
[10]姜宇,宝音贺西.强不规则天体引力场中的动力学研究进展[J].深空探测学报,2014,1(4):250-261.JIANG Y,BAOYIN H X.Research trend of dynamics in the gravitational field of irregular celestial body[J].Journal of Deep Space Exploration,2014,1(4):250-261.
[11]HOWELL K C,PERNICKA H J.Numerical determination of Lissajous orbits in the restrictedthree-body problem[J].Celestial Mechanics,1988,41:107-124.
[2]李俊峰,曾祥远,张韵.小行星的奇特动力学1)[J].力学与实践,2016,38(6):603-611.LI J F,ZENG X Y,ZHANG Y.Unique dynamics of asteroids 1)[J].Mechanics in Engineering,2016,38(6):603-611.
[3]CANALIAS E,GOMEZ G,MARCOTE M,et al.Assessment of mission design includingutilization of libration points and weak stability boudaries[R].ESOC Contract18142/04/NL/MV,Final Report,2004.
[4]FARQUHAR R,MUHONEN D,RICHARDSON D.Mission design for a halo orbiter of the Earth[J].Journal of Spacecraft and Rockets,1977,14:170-177.
[5]张振江,崔祜涛,崔平远.基于三阶解析解的小行星平衡点附近halo轨道确定方法研究[J].宇航学报,2011,32(2):277-283.ZHANG Z J,CUI H T,CUI P Y.Research on third-order analytical solution determination of halo orbits around equilibrium point of asteroid[J].Journal of Astronautics,2011,32(2):277-283.
[6]FOLTA D,RICHON K.Libration orbit mission design at L2:A MAPand NGST perspective[C]//AIAA/AAS Astrodynamics Conference.Boston:AIAA/AAS,1998.
[7]于洋,宝音贺西.小天体附近的轨道动力学研究综述[J].深空探测学报,2014,1(2):93-104.YU Y,BAOYIN H X.Review of orbital dynamics in the vicinity of solar system small celestial bodies scientific vision for future missions[J].Journal of Deep Exploration,2014,1(2):93-104.
[8]吴伟仁,崔平远,乔栋,等.嫦娥二号日地拉格朗日L2点探测轨道设计与实施[J].中国科学:科学通报,2012,57(21):1987-1991.WU W R,CUI P Y,QIAO D,et al.Design and performance of exploring trajectory to Sun-Earth L2 point for Chang’E-2 mission[J].Chin Sci Bull,2012,57(21):1987-1991.
[9]曾祥远,李俊峰,刘向东.不规则小天体引力场内的广义甩摆轨道[J].深空探测学报,2016,3(1):29-33.ZENG X Y,LI J F,LIU X D.Generalized flyby trajectories over irregular-shaped small bodies[J].Journal of Deep Space Exploration,2016,3(1):29-33.
[10]姜宇,宝音贺西.强不规则天体引力场中的动力学研究进展[J].深空探测学报,2014,1(4):250-261.JIANG Y,BAOYIN H X.Research trend of dynamics in the gravitational field of irregular celestial body[J].Journal of Deep Space Exploration,2014,1(4):250-261.
[11]HOWELL K C,PERNICKA H J.Numerical determination of Lissajous orbits in the restrictedthree-body problem[J].Celestial Mechanics,1988,41:107-124.