探测器月面起飞稳定性边界条件研究  

Study on take-off stability boundaries of lunar detector

作　　者：胡建国[1] 史耀祖 赵毅[1] 徐宏斌[1] HU Jianguo SHI Yaozu ZHAO Yi XU Hongbin(Xi＇an Modern Control Technology Research Institute, Xi＇an 710065, China)

机构地区：[1]西安现代控制技术研究所,西安710065

出　　处：《中国空间科学技术》2016年第5期40-47,共8页Chinese Space Science and Technology

摘　　要：探测器起飞稳定性是上升器月面起飞的重要性能指标,研究其特性对上升器返回地面具有重要的意义。选择上升器起飞稳定性主要影响因素,结合优化拉丁超立方试验设计方法和径向基神经网络建立了上升器起飞过程动力学近似模型,定量地判定出姿态角位移、姿态角速度对各影响因素的敏感程度。以上升器的姿态角位移和角速度分别为5°和5(°)/s为稳定判定条件,给出了单个影响因素的取值边界。编写了上升器起飞稳定性多因素边界条件分析程序,采用三维空间的方式建立了上升器起飞稳定性边界条件表达式,并以样例确定了起飞稳定性边界条件。The take-off stability of lunar detector is an important performance index of an ascender＇s taking off from the moon＇s surface. By choosing some main influence factors of take-off stability, the take-off dynamic approximation model of ascender was established combining with an optimal latin hypercube experimental design method and the RBF neural network, and the sensitivity of the factors for the angular displacement and velocity was quantitatively analyzed. Based on the stability criterion that the angular displacement and angular velocity of ascenders was 5° and 5 （°）/s respectively, the boundary values of a single influence factor were given. A program for multiple factors boundary analysis of the ascender take-off stability was compiled. The boundary expression of the ascender take-off stability is founded by the way of three-dimensional space, and the take-off stability boundaries were determined with a sample.

关 键 词：航天器结构与设计 月球探测器 起飞稳定性 近似模型 敏感度 临界条件 综合判据 

分 类 号：V423.6[航空宇航科学与技术—飞行器设计]