基于多参数偏差影响的航天器分离动力学仿真研究

RESEARCH ON DYNAMIC SIMULATION OF ON-ORBIT AIRCRAFT SEPARATION BASED ON MULTIPLE PARAMETERS DEVIATION INFLUENCE

航天器分离技术是深空探测领域的一项关键技术,航天器分离后的姿态受分离机构多个设计参数影响,分离后的相关运动性能指标具有不确定性.文章通过建立了航天器分离动力学仿真分析模型,开展了航天器分离过程的参数敏感性分析、分离安全包络分析、随机打靶分析以及多参数叠加的分离极限工况分析,以此评估分离机构多个设计参数的偏差对航天器分离后姿态的影响.文章的分析方法及结果解决了航天器姿态性能指标受多参数偏差影响的分离技术难题,为航天器分离方案设计和在轨分离过程提供了参考,也为航天器在轨高精度、高可靠分离的工程实施奠定了基础.

Separating technology is very important for the spacecraft exploring the deep space,and the attitude of separated spacecraft suffers from the design parameters of separating mechanism,the results of which make the motion performance index uncertain. Based on the dynamic model,the parameters sensibility analysis,separating safe distance analysis,parameter random test analysis,and multi-parameters combination limit case analysis are computed,the result of which is estimated on how the deviation of parameters affects the spacecraft attitude. The analytical method and results have resolved the difficult technology of spacecraft separation suffer from the influence of multi-parameters deviation,on which the reference is provided about high precision and high reliability separating design.