考虑燃料晃动效应的航天器自适应滑模姿态控制

针对一类带有球形储液箱的航天器，在将其等效为单摆模型的基础上，分析了系统方程的特点，将系统的状态变量分为两部分，并考虑到在航天器机动过程中燃料消耗作用的影响，导致系统方程中的三个重要参数发生变化.基于以上原因，设计了一种自适应分层滑模控制器，采用李雅普诺夫函数法求取自适应控制律和总的控制量，保证闭环系统的稳定性.最后通过仿真验证这种控制器设计不仅可以使系统姿态在短期时间之内达到稳态，还同时抑制了液体晃动产生的影响.

Adaptive Sliding-Mode Attitude Control of Spacecraft with Fuel Sloshing

In this paper, we analyze the dynamic characteristics of a spacecraft in low gravity with spherical tanks. The dynamic model of fuel sloshing is equivalent to a usual pendulum model. The state variables of the system are divided into two parts. In the case that three important parameters change with the fuel consumption, an adaptive hierarchical sliding-mode controller is designed in this paper. Using the Lyapunov method, parameter adaptive laws are derived, which guarantee the stability of the closed-loop system .The simulation results show that the system can achieve attitude tracking precision in a short time, as well as the fuel slosh is effectively suppressed.