基于区间算法的微小卫星微推力器阵列规模估计  

Estimation of Micro-Thruster Array Consumption for Micro-Satellite Based on Interval Algorithm

作　　者：闵家麒 朱宏玉[1] MIN Jiaqi ZHU Hongyu(School of Astronautics, Beihang University, Beijing 100191, China)

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《空间控制技术与应用》2017年第5期22-30,共9页Aerospace Control and Application

基　　金：国家自然科学基金资助项目(61403031)

摘　　要：针对以固体微推力器阵列为执行机构的微小卫星初入轨姿态控制需求,研究固体微推力器阵列规模的估计方法.在设计了微推力器阵列单元调用规则和姿态控制律后,考虑微推力器阵列各单元冲量输出的不确定性,使用区间数表示微推力器单元的力矩输出,引入区间算法对初入轨的消旋和姿态捕获两个主要过程中微推力器单元的消耗情况进行计算.利用区间数的不相关性,改善区间计算过程,减小了由区间积分导致的区间扩张.仿真分析表明,提出的固体微推力器阵列规模估计方法可以给出预定入轨条件下的阵列规模需求,且其结果不依赖于微推力器单元力矩输出的概率特性.A method for solid propellant micro-thruster array consumption estimation is proposed in this paper for attitude control of micro-satellite in orbit entry stage. The micro-thruster unit call rule and atti- tude control laws of velocity damping and attitude capture are designed. Considering the uncertainty of each micro-thruster unit impulse output, we use the interval number to represent the micro-thruster unit torque output and then estimate the consumption of the micro-thruster unit for attitude control with interval algorithm. By means of the irrelevance of interval number, the interval computation process is improved, and the interval expansion induced by the interval integral is reduced. Numerical simulations demonstrate that the estimation method is not dependent on the probability characteristic of the micro-thruster unit torque output.

关 键 词：姿态控制 执行机构设计 固体微推力器阵列 区间算法 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]