内编队重力场测量卫星微推力器姿轨一体化控制  

Application of Microthrusters of Integrated Orbit and Attitude Control of Inner-formation Gravity Field Measurement Satellite

作　　者：吉莉[1] 刘昆[1] 项军华[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2011年第6期89-94,共6页Journal of National University of Defense Technology

基　　金：国家自然科学基金资助项目(11002076);国家部委资助项目(51320010201)

摘　　要：内编队重力场测量卫星通过精密定轨和相对状态测量实现高精度高分辨率地球重力场测量。这两项技术都依赖于精密编队控制和姿态控制。稳态工作期间,要求相对位移必须控制在厘米量级内,外卫星对地定向精度优于0.1°。姿轨一体化控制的目标是利用微推力器保障稳态工作期间的科学测量。基于带推力器布局的耦合线性模型进行了内编队重力场测量卫星全推力设计。基于模型预测控制算法实现了卫星的姿轨一体化控制,仿真结果证实全推力器一体化控制方案的可行性与有效性。The inner-formation gravity field measurement satellite was proposed to measure Earth＇s gravity field with high accuracy and spatial resolution through precise orbit determination and relative state measurement.Both techniques relied on precise formation control and accurate attitude control,during steady-state phase,where the relative displacement had to be suppressed down to centimeter,and the outer-satellite attitude had to be earth-oriented with 0.1 degree accuracy.The integrated orbit and attitude control aims to guarantee the scientific measurement during steady-state phase,applying micro-thrusters.The all-propulsion design was processed on a coupled linear model with thruster layout;the integrated orbit and attitude control was implemented based on model predictive control（MPC） algorithm.Simulation results demonstrate the feasibility and validity of this integrated control scheme with micro-thrusters.

关 键 词：内编队 姿轨一体化控制 全推力 

分 类 号：V239.1[航空宇航科学与技术—航空宇航推进理论与工程]