推力器布设对控制误差的影响分析  

Analysis of Effect of Thruster Configuration on Control Error

作　　者：岳晓奎[1] 段辰璐[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《宇航学报》2011年第7期1522-1526,共5页Journal of Astronautics

基　　金：教育部新世纪优秀人才支持计划(NCET-06-0886);高等学校博士学科点专项科研基金(20106102110003)

摘　　要：航天器推力系统发动机数目及其构型的选择直接影响控制系统的精度和完成要求任务的燃料消耗量。对航天器六自由度控制的推力分配问题进行了研究,参考卫星导航系统中几何精度衰减因子的定义,提出了发动机构型精度衰减因子的概念,用于定义发动机相对几何关系引起的执行误差与分配误差间的比例关系。通过矩阵理论分析得到了构型精度衰减因子随参与分配发动机数目增加而增加的结论,并通过仿真计算对相关结论进行了验证,为航天器发动机数目及其构型的选择提供了理论参考。The control accuracy as well as the propellant consumption is directly affected by the number of thrusters and their configuration.This paper makes a research on the thrust allocation scheme of a spacecraft.On the analogy of GDOP used in satellite navigation system,the concept of thruster configuration dilution of precision（CDOP） is proposed to define the ratio between the thrust allocation error and the error caused by the thruster configuration.The conclusion that the CDOP increases as the number of thrusters is obtained by analysis of matrix theory.Finally,the CDOP concept and the conclusion presented are validated by a simulation,and can provides a reference for the selection of the number of the thrusters and their configuration.

关 键 词：推力器布设 推力分配 构型精度衰减因子 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]