小天体多目标多模式探测任务设计
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摘要
多目标多模式小天体探测具有降低任务成本、增加科学回报的优点,本文针对多目标多模式小天体探测任务中摄动敏感、约束复杂以及推力幅值变化等任务规划的设计难题,研究了地球准卫星采样返回以及主带彗星交会探测任务的转移轨道设计问题.首先,介绍了探测目标的科学价值并根据任务约束给出探测任务构想.其次,基于椭圆型限制性三体问题,考虑星历、发射能量和采样返回再入速度等约束,设计并优化了地球准小行星目标的多脉冲采样返回轨道,实现地球发射与返回段和星际转移段全过程的精确飞行设计.最后,根据任务约束,推导了推力幅值可变的最优小推力转移轨道的一阶必要条件并给出考虑借力约束的初值选取方法.以采样后火星借力探测主带彗星为例,求解并分析了最大推力幅值衰减的小推力交会轨道.本文的研究方法可为我国未来的深空探测任务提供参考.
Multi-target exploration to small bodies has the advantages of reducing mission cost and increasing scientific return. It will be widely used in the future small body exploration missions. This paper investigates the problem of perturbation sensitivity, complicated constraints and changeable thrust, which may be faced in the multi-target exploration mission.The Earth quasi-satellite sampling return and main-belt comet rendezvous missions are studied. First, based on the mission constraints, the mission design schedule and relevant constraints are given. Then, the multi-impulse asteroid sampling return trajectory is investigated in the elliptical three body model. Considering the gravitational perturbation of Earth, the integral trajectory design consist of Earth escape phase, interplanetary transfer phase, and Earth reentry phase is proposed. The trajectory design is divided into two parts. The optimal preliminary transfer opportunity is firstly searched in two-body problem and is transferred to the elliptical three body model. The differential correction scheme is applied to correct the error caused by Earth gravity perturbation. The trajectory for the Earth quasi-satellite 2016 HO3 is designed. Finally, considering the engineering constraints, the first-order necessary condition of the changeable lowthrust trajectory are derived, where both the thrust and special impulse change with the distance to Sun. By introducing the B-plane parameters, the initial states determination under the constraint of the gravity assist is developed. Based on the homotopy method, the low-thrust optimal trajectory after Mars gravity assist to the main belt comet 133 P are designed and compared with constant low thrust trajectory. The proposed multi-target exploration scheme and the orbit design method can provide a reference for future small bodies exploration missions in China.
Multi-target exploration to small bodies has the advantages of reducing mission cost and increasing scientific return. It will be widely used in the future small body exploration missions. This paper investigates the problem of perturbation sensitivity, complicated constraints and changeable thrust, which may be faced in the multi-target exploration mission.The Earth quasi-satellite sampling return and main-belt comet rendezvous missions are studied. First, based on the mission constraints, the mission design schedule and relevant constraints are given. Then, the multi-impulse asteroid sampling return trajectory is investigated in the elliptical three body model. Considering the gravitational perturbation of Earth, the integral trajectory design consist of Earth escape phase, interplanetary transfer phase, and Earth reentry phase is proposed. The trajectory design is divided into two parts. The optimal preliminary transfer opportunity is firstly searched in two-body problem and is transferred to the elliptical three body model. The differential correction scheme is applied to correct the error caused by Earth gravity perturbation. The trajectory for the Earth quasi-satellite 2016 HO3 is designed. Finally, considering the engineering constraints, the first-order necessary condition of the changeable lowthrust trajectory are derived, where both the thrust and special impulse change with the distance to Sun. By introducing the B-plane parameters, the initial states determination under the constraint of the gravity assist is developed. Based on the homotopy method, the low-thrust optimal trajectory after Mars gravity assist to the main belt comet 133 P are designed and compared with constant low thrust trajectory. The proposed multi-target exploration scheme and the orbit design method can provide a reference for future small bodies exploration missions in China.
引文
1 de la Fuente Marcos C,de la Fuente Marcos R.Asteroid(469219)2016HO3,the smallest and closest Earth quasi-satellite.Mon Not R Astron Soc,2016,462:3441-3456,arXiv:1608.01518
2 Jewitt D,Ishiguro M,Weaver H,et al.Hubble space telescope investigation of main-belt comet 133p/elst-pizarro.Astronom J,2014,147:117,arXiv:1402.5571
3 Hulkower N D,Lau C O,Bender D F.Optimum two-impulse transfers for preliminary interplanetary trajectory design.J Guidance Control Dyn,2015,7:458-461
4 Qiao D,Cui H,Cui P.Evaluating accessibility of near-Earth asteroids via Earth gravity assists.J Guidance Control Dyn,2006,29:502-505
5 Cui P Y,Qiao D,Cui H T,et al.Target selection and transfer trajectories design for exploring asteroid mission.Sci China Technol Sci,2010,53:1150-1158
6 Chen Y,Baoyin H X,Li J F.Design and optimization of a trajectory for Moon departure near Earth asteroid exploration.Sci China-Phys Mech Astron,2011,54:748-755
7 Wang Y M,Qiao D,Cui P Y.Trajectory design for the transfer from the Lissajous orbit of Sun-Earth system to asteroids.AMM,2013,390:478-484
8 Bulirsch R,Callies R.Optimal trajectories for a multiple rendezvous mission to asteroids.Acta Astronaut,1992,26:587-597
9 Chen Y,Baoyin H X,Li J F.Target analysis and low-thrust trajectory design of Chinese asteroid exploration mission(in Chinese).Sci Sin-Phys Mech Astron,2011,41:1104-1111[陈杨,宝音贺西,李俊峰.我国小行星探测目标分析与电推进轨道设计.中国科学:物理学力学天文学,2011,41:1104-1111]
10 Chen Y,Baoyin H,Li J.Accessibility of main-belt asteroids via gravity assists.J Guidance Control Dyn,2014,37:623-632
11 Yang H,Li J,Baoyin H.Low-cost transfer between asteroids with distant orbits using multiple gravity assists.Adv Space Res,2015,56:837-847
12 Bertrand R,Epenoy R.New smoothing techniques for solving bang-bang optimal control problems--Numerical results and statistical interpretation.Optim Control Appl Meth,2002,23:171-197
13 Jiang F,Tang G,Li J.Improving low-thrust trajectory optimization by adjoint estimation with shape-based path.J Guidance Control Dyn,2017,40:3282-3289
14 Li J F,Baoyin H X,Jiang F H.Dynamics and Control of Interplanetary Flight.Beijing:Tsinghua University Press,2014.204-205[李俊峰,宝音贺西,蒋方华.深空探测动力学与控制.北京:清华大学出版社,2014,204-205]
1)http://www.cnsa.gov.cn/n6758823/n6758839/c6805886/content.html
2 Jewitt D,Ishiguro M,Weaver H,et al.Hubble space telescope investigation of main-belt comet 133p/elst-pizarro.Astronom J,2014,147:117,arXiv:1402.5571
3 Hulkower N D,Lau C O,Bender D F.Optimum two-impulse transfers for preliminary interplanetary trajectory design.J Guidance Control Dyn,2015,7:458-461
4 Qiao D,Cui H,Cui P.Evaluating accessibility of near-Earth asteroids via Earth gravity assists.J Guidance Control Dyn,2006,29:502-505
5 Cui P Y,Qiao D,Cui H T,et al.Target selection and transfer trajectories design for exploring asteroid mission.Sci China Technol Sci,2010,53:1150-1158
6 Chen Y,Baoyin H X,Li J F.Design and optimization of a trajectory for Moon departure near Earth asteroid exploration.Sci China-Phys Mech Astron,2011,54:748-755
7 Wang Y M,Qiao D,Cui P Y.Trajectory design for the transfer from the Lissajous orbit of Sun-Earth system to asteroids.AMM,2013,390:478-484
8 Bulirsch R,Callies R.Optimal trajectories for a multiple rendezvous mission to asteroids.Acta Astronaut,1992,26:587-597
9 Chen Y,Baoyin H X,Li J F.Target analysis and low-thrust trajectory design of Chinese asteroid exploration mission(in Chinese).Sci Sin-Phys Mech Astron,2011,41:1104-1111[陈杨,宝音贺西,李俊峰.我国小行星探测目标分析与电推进轨道设计.中国科学:物理学力学天文学,2011,41:1104-1111]
10 Chen Y,Baoyin H,Li J.Accessibility of main-belt asteroids via gravity assists.J Guidance Control Dyn,2014,37:623-632
11 Yang H,Li J,Baoyin H.Low-cost transfer between asteroids with distant orbits using multiple gravity assists.Adv Space Res,2015,56:837-847
12 Bertrand R,Epenoy R.New smoothing techniques for solving bang-bang optimal control problems--Numerical results and statistical interpretation.Optim Control Appl Meth,2002,23:171-197
13 Jiang F,Tang G,Li J.Improving low-thrust trajectory optimization by adjoint estimation with shape-based path.J Guidance Control Dyn,2017,40:3282-3289
14 Li J F,Baoyin H X,Jiang F H.Dynamics and Control of Interplanetary Flight.Beijing:Tsinghua University Press,2014.204-205[李俊峰,宝音贺西,蒋方华.深空探测动力学与控制.北京:清华大学出版社,2014,204-205]
1)http://www.cnsa.gov.cn/n6758823/n6758839/c6805886/content.html