充液航天器目标跟踪自适应控制

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.

Adaptive Control of Target Tracking for Liquid-Filled Spacecraft

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 character...