基于一次性微冲量推力器阵列的卫星低频振动抑制与控制  

The Low Frequency Vibration Suppression and Control of Satellite Based on Disposable Micro Impulse Thruster Array

作　　者：魏延明[1,2] 刘旭辉[1] 樊子辰[3] 

机构地区：[1]北京控制工程研究所,北京100080 [2]哈尔滨工业大学能源科学与工程学院,哈尔滨150001 [3]北京航空航天大学宇航学院,北京100191

出　　处：《空间控制技术与应用》2017年第3期1-6,14,共7页Aerospace Control and Application

基　　金：总装预研基金资助项目(9140A20050315HT05001)

摘　　要：为了解决挠性卫星受扰后的主动振动控制问题,提出将一次性微冲量推力器阵列(DMITA)作为控制执行器安装在卫星太阳帆板上,其具有体积小、成本低、功耗低的特点.介绍一次性微冲量推力器主动振动控制系统(DMITAVCS)的初步应用方案,用混合坐标法推导装有DMITAVCS的挠性卫星姿态动力学方程,并给出能量最优的DMITA位置配置准则.数值仿真结果表明DMITAVCS能够快速抑制挠性卫星受扰后姿态和帆板的振动,主要得益于安装在帆板上的一次性微冲量推力器阵列(DMITA)能够产生较大的姿态驱动力臂.To study the vibration control of satellite with flexible solar panels under disturbance,the disposable micro impulse thruster array（ DMITA） is propose to settle on the solar panels as actuators for active vibration control. The DMITA is characterized by small size,low cost and low energy consumption.The application scheme of disposable micro impulse thruster active vibration control system（ DMITAVCS）is introduced and the attitude dynamic equations of flexible satellite with DMITAVCS is derived by hybrid coordinate method. The optimal energy principle for settlement location of DMITA is also analyzed. Numerical simulations demonstrate that the DMITAVCS can suppress the vibration of flexible satellite in a short time,which benefits from the long arm of force produced by the DMITA settled on the solar panels.

关 键 词：主动振动控制 太阳帆板 一次性微冲量推力器阵列 

分 类 号：V448[航空宇航科学与技术—飞行器设计]