基于微型固体推力器阵列的轨道控制点火算法

推进技术 ›› 2011, Vol. 32 ›› Issue (3): 301-306.

• 气动热力学 • 下一篇

基于微型固体推力器阵列的轨道控制点火算法

刘旭辉,方蜀州,王玉林,李洪美

北京理工大学宇航学院,北京 100081;北京理工大学宇航学院,北京 100081;北京理工大学宇航学院,北京 100081;北京理工大学宇航学院,北京 100081

发布日期:2021-08-15
作者简介:刘旭辉(1983—),男,博士生,研究领域为微小型姿轨控动力系统。E-mail:xhliu@bit.edu.cn
基金资助:
“十一五”民用航天预先研究项目(D2220062901)。

Ignition algorithm of solid propellant micro-thruster array for orbit control

School of Aerospace Engineering, Beijing Inst. of Technology, Beijing 100081, China;School of Aerospace Engineering, Beijing Inst. of Technology, Beijing 100081, China;School of Aerospace Engineering, Beijing Inst. of Technology, Beijing 100081, China;School of Aerospace Engineering, Beijing Inst. of Technology, Beijing 100081, China

Published:2021-08-15

摘要/Abstract

摘要： 为了解决基于微型固体推力器阵列轨道控制的推力器组合点火问题,优化了阵列布局,使其适用于轨道控制,得出了推力器坐标位置分布律。在此基础上研究了推力器阵列组合点火算法,建立了相应数学模型,进行了算法验证。仿真结果表明,设计的推力器阵列优化方案能够满足皮纳卫星轨道控制要求,所建数学模型能有效解决点火问题,设计的算法能够实现较快寻址。

关键词: 微型固体推力器阵列;点火算法;轨道控制;优化算法

Abstract: To solve the problem of combined ignition of solid propellant micro-thruster array for orbit control, the layout of micro-thruster array was further optimized to enhance its applicability, and the distribution rule of thruster array was obtained. Combined ignition algorithm with thruster array was proposed. The mathematical model was established and the algorithm was verified. The simulation results show that the requirements of micro-satellite orbit control can be satisfied by the optimal design of thruster array. The mathematic model can solve the ignition problem, and ignition thruster can be addressed quickly by the proposed algorithm.

Key words: Solid propellant micro-thruster array; Ignition algorithm; Orbit control; Optimization algorithm

刘旭辉,方蜀州,王玉林,李洪美. 基于微型固体推力器阵列的轨道控制点火算法[J]. 推进技术, 2011, 32(3): 301-306.

基于微型固体推力器阵列的轨道控制点火算法

Ignition algorithm of solid propellant micro-thruster array for orbit control

可视化

被引次数

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 0

编辑推荐

Metrics

本文评价