模块化航天器姿态控制系统仿真研究  

Simulation research on attitude control system for modular spacecraft

作　　者：贺广松 李新洪 王谦 张治彬 安继萍 HE Guangsong;LI Xinhong;WANG Qian;ZHANG Zhibin;AN Jiping(School of Graduate,Aerospace Engineering University,Beijing 101416,China;Department of Space Equipment,Aerospace Engineering University,Beijing 101416,China)

机构地区：[1]航天工程大学研究生院,北京101416 [2]航天工程大学航天装备系,北京101416

出　　处：《现代电子技术》2018年第18期131-134,共4页Modern Electronics Technique

摘　　要：以快速响应为背景,对模块化航天器姿态控制系统进行研究。首先建立集成干扰力矩、姿态运动学、姿态动力学、控制律及飞轮、推力器两种执行机构的Simulink模型,然后应用实时仿真机对模型进行仿真。结果表明:不同执行机构的姿态控制系统能够完成对卫星姿态的实时控制并且在进行姿态调整时各有优势,最后以实时仿真机为基础设计了模块化航天器显示系统,实现了模块化航天器分系统状态和运行场景可视化。Taking rapid response as the background,an attitude control system for the modular spacecraft is studied.The Simulink model integrating the disturbance torque,attitude kinematics,attitude dynamics,control law,and two actuators of fly-wheel and thruster is established.The real-time simulation machine is applied to simulate the model.The result shows that the at-titude control system with different actuators can accomplish real-time control of satellite attitudes and each actuator has its own advantage in attitude adjustment.On the basis of the real-time simulator,the display system of the modular spacecraft is de-signed to realize visualization for subsystem status and operation scenario of the modular spacecraft.

关 键 词：模块化航天器 姿态控制 SIMULINK 执行机构 显示系统 可视化 

分 类 号：TN876-34[电子电信—信息与通信工程] TP391[自动化与计算机技术—计算机应用技术]