喷气/偏置动量轮联合微小卫星三轴稳定控制  

Combined Control for Three-axis Stabilization of Micro-satellite Using Thrusters and Single Pitch Bias Momentum Wheel

作　　者：刘海颖[1] 王惠南[2] 陈志明[2] 叶伟松[1] 

机构地区：[1]南京航空航天大学高新技术研究院,南京210016 [2]南京航空航天大学自动化学院,南京210016

出　　处：《系统仿真学报》2009年第7期2023-2026,共4页Journal of System Simulation

摘　　要：针对偏置动量轮加喷气的微小卫星姿态控制方案,给出了LQG和Lyapunov控制的两种三轴稳定控制方法。首先以轨道系为参考建立了卫星、偏置动量轮以及喷气系统模型,在此基础上设计了两种喷气/动量轮联合控制律。仿真结果表明两种控制方法,将动量轮和采用PWM技术的喷气系统进行联合控制,与单独动量轮俯仰控制、喷气进行滚动-偏航控制的传统方法相比较,具有更高的控制精度,并且减少喷气系统的燃料消耗,同时还可以减少动量轮饱和的机会。Two three-axis stabilization control methods using LQG and Lyapunov control were given for micro-satellite containing a pitch bias momentum wheel and thrusters. The satellite model, as well as the momentum wheel and thrusters model were established refer to the orbit frame. Based on these models, two controllers combined thrusters with a single pitch bias momentum wheel were designed based on it. Simulating result indicates the combined PWM thrusters and wheel controllers, compared with the traditional method using momentum to control the pitch axis and thrusters for roll/yaw axis, have high control precision with littler fuel consuming, and can reduce the chance of momentum wheel saturation.

关 键 词：微小卫星 姿态稳定 喷气系统 偏置动量轮 LQG控制 Lyapunov控制 

分 类 号：V448[航空宇航科学与技术—飞行器设计]