| 小天体着陆动力学参数不确定性影响分析 |
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| 作者姓名： | 袁旭 朱圣英 乔栋 崔平远 |
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| 作者单位： | 北京理工大学小天体探测与防御实验室,北京100081;飞行器动力学与控制教育部重点实验室,北京100081;北京理工大学小天体探测与防御实验室,北京100081;飞行器动力学与控制教育部重点实验室,北京100081;北京理工大学小天体探测与防御实验室,北京100081;飞行器动力学与控制教育部重点实验室,北京100081;北京理工大学小天体探测与防御实验室,北京100081;飞行器动力学与控制教育部重点实验室,北京100081 |
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| 基金项目： | 国家重点基础研究发展计划(973计划)(2012CB720000);国家自然科学基金(61304248);基础科研计划(B2220110012);民用
航天预先研究计划 |
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| 摘 要： | 针对小天体不规则程度高、引力场复杂,且物理参数存在较高不确定性的问题,基于小天体着陆动力学方程线性化近似解析解,对各动力学参数不确定性的影响进行了分析。考虑动力学方程线性化带来的误差,引入线性化误差补偿校正方法,建立了探测器轨迹对动力学参数不确定性的敏感度方程。以小行星Eros 433为例,重点分析了目标小天体质量、自转角速度、引力势函数系数,以及探测器初始状态、推力加速度等动力学参数不确定性对探测器着陆轨迹的影响。数学仿真分析表明,针对本文选取的目标小天体,推力加速度扰动为主要影响因素,探测器初始状态的不确定性为次要影响因素,其他参数扰动的影响较小。
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| 关 键 词： | 小天体 着陆 参数不确定性 敏感性分析 |
| 收稿时间： | 2013/11/1 0:00:00 |
| 修稿时间： | 2013/12/30 0:00:00 |
Impact Analysis of Dynamic Parameters Uncertainty
on Small Celestial Body Landing |
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| Authors: | YUAN Xu ZHU Shengying QIAO Dong and CUI Pingyuan |
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| Institution: | Laboratory of Asteroid Exploration and Defense,Beijing Institute of Technology,Beijing100081,China;Key Laboratory of Dynamics and Control of Flight Vehicle,Ministry of Education,Beijing100081,China;Laboratory of Asteroid Exploration and Defense,Beijing Institute of Technology,Beijing100081,China;Key Laboratory of Dynamics and Control of Flight Vehicle,Ministry of Education,Beijing100081,China;Laboratory of Asteroid Exploration and Defense,Beijing Institute of Technology,Beijing100081,China;Key Laboratory of Dynamics and Control of Flight Vehicle,Ministry of Education,Beijing100081,China;Laboratory of Asteroid Exploration and Defense,Beijing Institute of Technology,Beijing100081,China;Key Laboratory of Dynamics and Control of Flight Vehicle,Ministry of Education,Beijing100081,China |
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| Abstract: | To the challenge of high degree irregularity,complex gravity field and relatively high degree of physical parameters uncertainty of small celestial bodies,the impact of dynamic parameters uncertainty is analyzed,based on the approximate linearized analytical solution of the small celestial body landing dynamic equations.A calibrating method is used to compensate the errors brought in by linearization.And the sensitivity equations of
spacecraft trajectories to dynamic parameters are established.Taking the asteroid Eros 433 as an example,the impact of the uncertainty of the mass,rotation rate and gravitational potential coefficients of the target body on the spacecraft landing trajectory,the initial state of the spacecraft and the thrust acceleration are analyzed elaborately.Mathematical simulation shows that for this selected target body,the thrust acceleration disturbance is the primary factor of such impact,and the initial state of the spacecraft the secondary one.And the impact of other parameters are relatively small |
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| Keywords: | small celestial body landing parameters uncertainty sensitivity analysis |
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