摘要
对于在零重力环境下受到横向控制力和俯仰控制力矩作用的带球形贮液箱的航天器模型,研究了其在平面运动的动力学特性.将晃动液体等效为单摆模型,利用Lagrange方法建立了系统动力学方程并且将其转化为状态变量方程形式;应用微分几何原理,以单输入—单输出系统(SISO)为例,研究了系统的非线性动力学特性,并进一步针对目标跟踪问题设计了SISO系统基于线性化模型的控制策略.研究结果表明:对于液体晃动-航天器姿态耦合动力学系统采用极点配置间接自校正控制策略能够实现姿态角的镇定及跟踪.
For the spacecraft model with a spherical fuel tank controlled by a horizontal force and a pitch moment under the condition of the zero gravity,the dynamics performance about a liquid-filled spacecraft moving in a plane is studied.With the single pendulum model of a typical spacecraft with fuel sloshing,the dynamics equations are derived based on Lagrange method,and then are transformed into the form of state variable equations.In the case of single input-single output（SISO）,the nonlinear dynamics characteristics of the system are discussed by means of the differential geometry theory.Furthermore,a control strategy for the target tracking is designed on the basis of linearization model of SISO system.The result indicates that the pole placement-based indirect adaptive control strategy can realize attitude stabilization and tracking for liquid sloshing-spacecraft attitude coupled dynamics system.
出处
《空间控制技术与应用》
2011年第1期40-44,共5页
Aerospace Control and Application
基金
国家自然科学基金(10772026
11072030)资助项目
关键词
充液航天器
姿态控制
自校正控制
liquid-filled spacecraft
attitude control
self-tuning control
