小卫星对上面级定向的姿控设计与验证  

Design and Verification of Small Satellite Attitude Control to Upper Stage Rocket

作　　者：张宏德 赵心欣 卢伟 Zhang Hongde;Zhao Xinxin;Lu Wei(Beijing Institute of Astronautical System Engineering, Beijing100076,China)

机构地区：[1]北京宇航系统工程研究所,北京100076

出　　处：《计算机测量与控制》2019年第5期91-95,共5页Computer Measurement &Control

摘　　要：文章针对小卫星对上面级的快速定向问题,设计了小卫星对上面级定向的姿控方案,设计了基于陀螺的4阶龙格库塔积分算法与递阶饱和PD控制算法,首先通过数学仿真初步验证了姿控方案、姿控算法设计的正确性;在此基础上,搭建了小卫星姿控系统半实物仿真平台,并开发了相应的仿真软件,进行了飞轮开环跟踪与飞轮闭环跟踪的小卫星姿控系统半实物仿真,进一步验证了姿控方案、姿控算法设计的正确性;最后经过飞行试验,根据实际飞行结果,证明了姿控系统设计的正确性。In this paper,aiming at the problem of rapid orientation of small satellites to the upper stage rocket,the attitude control scheme of small satellites to the upper stage rocket is designed,and the fourth order Runge-Kutta integral algorithm and hierarchical saturated PD control algorithm based on gyro are designed.Firstly,the correctness of the attitude control scheme and attitude control algorithm is preliminarily verified through mathematical simulation.On this basis,a semi-physical simulation platform of the small satellite attitude control system is built,and corresponding simulation software is developed to carry out semi-physical simulation of the small satellite attitude control system of flywheel open-loop tracking and flywheel closed-loop tracking,which further verifies the correctness of the attitude control scheme and attitude control algorithm design.Finally,the correctness of the attitude control system is proved by the fly test.

关 键 词：姿控系统设计 递阶饱和PD控制算法 半实物仿真 飞行试验 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]