含多正弦扰动的航天器无拖曳控制系统性能极限研究  

Performance limitations for spacecraft drag-free control system in the presence of multi-sinusoidal disturbance

作　　者：邹奎[1,2] 苟兴宇[1,2] 范达 

机构地区：[1]北京控制工程研究所,北京100190 [2]空间智能控制技术重点实验室,北京100190 [3]钱学森空间技术实验室,北京100094

出　　处：《控制理论与应用》2017年第4期449-456,共8页Control Theory & Applications

基　　金：国家自然科学基金项目(51505472)资助~~

摘　　要：本文研究了航天器无拖曳控制系统的性能极限问题.将空间环境扰动描述为一个阶跃分量、一个平稳随机分量和多个正弦分量的线性组合,利用残余非保守力的稳态方差度量扰动抑制性能,并运用Wiener-Hopf设计方法求解最小灵敏度函数.为确保残余非保守力的渐近平稳性,将最小灵敏度函数表示为反馈系统的频域拓扑结构,并推导了闭环系统的极限指标.结合无拖曳控制指标,讨论了加速度计模式下的传感器、执行器的指标分解问题.This paper is to contribute to the understanding of performance limitations for spacecraft drag-free control system. Environmental disturbance is modeled as a linear combination of a step component, a stationary stochastic component and several sinusoids with different frequencies. Disturbance rejection is measured by the steady-state variance of the residual non-gravitational force, and Wiener-Hopf design method is used to solve the minimizing sensitivity function. To guarantee the asymptotic stationary of the residual non-gravitational force, the minimizing sensitivity function accounting for the toplogical structure of the feedback system is used to derive the limiting performance. By using the drag-free control requirement, performance budgeting of actuator and sensor in accelerometer mode are discussed.

关 键 词：无拖曳控制 谱分解 WIENER-HOPF 指标分解 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]