logo

SCIENTIA SINICA Physica, Mechanica & Astronomica, Volume 49, Issue 8: 084508(2019) https://doi.org/10.1360/SSPMA-2019-0028

Dynamics and control of proximity operations for asteroid exploration mission

More info
  • ReceivedJan 25, 2019
  • AcceptedMar 21, 2019
  • PublishedJun 10, 2019
PACS numbers

Abstract

In asteroid exploration mission, the spacecraft needs to execute a series of proximity operations such as approaching, accompany flying, orbiting and hovering, which are the premise and key points to achieve asteroid sample return. Based on the concept of Chinese future asteroid exploration missions, this paper studies the dynamics and control of the proximity operation. First, considering the path and line-of-sight angle constraint, the sliding guidance law is used to design the multi-impulse approaching trajectory. A reconstruction iterative strategy is proposed for the perturbation effect including the irregular shaped gravity, solar radiation pressure, and three-body perturbations. Second, in order to obtain the preliminary physical characteristics of the asteroid, the accompany orbit and slow hyperbolic flybys are designed. The equation of the relative distance and velocity of the accompany orbit is established and the families of accompany orbits with different offsets and sizes are discussed. The spin rate and preliminary shape model of the asteroid can be established during the accompany phase. Then, by slow-flybys, the mass and coefficients of the gravity field of the asteroid can be obtained. The relation between flyby velocity, flyby distance, and flyby duration are found to achieve the global mapping of the asteroid. Several kinds of slow-flyby trajectory are presented. Finally, a self-adaptive control law is designed and proved to achieve the stable hovering at any point or region near the asteroid against varies perturbations and model uncertainty. Based on the control law, the fixed-point hovering and local region hovering are investigated respectively, which can be utilized to precise local exploration and imaging. The simulation results of asteroid 2016 HO3 verify the feasibility of the proposed method. The study can provide a reference for Chinese future asteroid exploration missions.


Funded by

国家自然科学基金(11572038,11772050)

长江学者奖励计划(青年项目)


References

[1] de la Fuente Marcos C, de la Fuente Marcos R. Asteroid (469219) 2016 HO3, the smallest and closest Earth quasi-satellite. Mon Not R Astron Soc, 2016, 462: 3441-3456 CrossRef ADS arXiv Google Scholar

[2] Gong S P, Li J F, Baoyin H X. Utilization of constant low thrust for control of spacecraft near asteroid (in Chinese). Sci Sin-Phys Mech Astron, 2011, 41: 1224-1229 CrossRef ADS Google Scholar

[3] Cui H Y, Li J F, Gao Y F. Error analysis of Lawden’s equation in satellite formation flying (in Chinese). Eng Mech, 2006, 23: 188–192 [崔海英, 李俊峰, 高云峰. 卫星编队飞行中Lawden方程的误差分析. 工程力学, 2006, 23: 188–192]. Google Scholar

[4] Takahashi Y, Scheeres D J. Small-body postrendezvous characterization via slow hyperbolic flybys. J Guid Control Dyn, 2011, 34: 1815-1827 CrossRef ADS Google Scholar

[5] Anderson J D. Feasibility of determining the mass of an asteroid from a spacecraft flyby. In: International Astronomical Union Colloquium, Volume 12 (Physical Studies of Minor Planets). NASA Special Publication, 1971. 577–583. Google Scholar

[6] Takahashi Y, Broschart S, Lantoine G. Flyby characterization of lower-degree spherical harmonics around small bodies. In: AIAA/AAS Astrodynamics Specialist Conference, 4–7, August 2014. San Diego, 2014. Google Scholar

[7] Jiang Y, Li J F. Secret of equilibrium points in the vicinity of an asteroid (in Chinese). Mech Eng, 2017, 39: 509–515 [姜宇, 李俊峰. 小天体平衡点之谜. 力学与实践, 2017, 39: 509–515]. Google Scholar

[8] Jiang Y, Baoyin H X, Wang X Y, et al. Order and chaos near equilibrium points in the potential of rotating highly irregular-shaped celestial bodies. Nonlinear Dyn, 2016, 83: 231-252 CrossRef Google Scholar

[9] Yu Y, Baoyin H X. Generating families of 3D periodic orbits about asteroids. Mon Not R Astron Soc, 2012, 427: 872-881 CrossRef ADS Google Scholar

[10] Scheeres D J. Orbital mechanics about small bodies. Acta Astronaut, 2012, 72: 1-14 CrossRef ADS Google Scholar

[11] Li X, Qiao D, Li P. Bounded trajectory design and self-adaptive maintenance control near non-synchronized binary systems comprised of small irregular bodies. Acta Astronaut, 2018, 152: 768-781 CrossRef ADS Google Scholar

[12] Min Y Y, Liu Y G. Barbalat Lemma and its application in analysis of system stability (in Chinese). J Shandong Univ, 2007, 37: 51–55 [闵颖颖, 刘允刚. Barbalat引理及其在系统稳定性分析中的应用. 山东大学学报, 2007, 37: 51–55]. Google Scholar

[13] Yang H W, Bai X L, Baoyin H X. Rapid generation of time-optimal trajectories for asteroid landing via convex optimization. J Guid Control Dyn, 2017, 40: 628-641 CrossRef ADS Google Scholar

[14] Yang H W, Bai X L, Baoyin H X. Rapid trajectory planning for asteroid landing with thrust magnitude constraint. J Guid Control Dyn, 2017, 40: 2713-2720 CrossRef ADS Google Scholar

Copyright 2019 Science China Press Co., Ltd. 《中国科学》杂志社有限责任公司 版权所有

京ICP备18024590号-1