中文摘要：

挠性充液航天器的动力学特性十分复杂．由于喷气脉冲存在调制环节，使得控制输入属于强非线性输入，该特点增加了控制系统的分析和设计难度．针对轨道转移期间挠性充液航天器的姿态控制问题，在动力学建模和模型变换的基础上，提出了一种基于直接型自适应模糊逻辑系统和误差补偿的改进控制算法．在控制律的设计中，将自适应模糊系统直接用作系统的主控制律，并引入基于饱和函数的稳定补偿律进一步提高控制性能．利用完整的三通道数学模型进行数学仿真，仿真结果验证了算法的有效性．

英文摘要：

The dynamics of a flexible liquid-fueled spacecraft are very complicated. The control input of the system is strongly nonlinear because of the jet pulse modulator, which increases the difficulty of analysis and design. For attitude control of the flexible liquid-fueled spacecraft during orbit maneuvering, an improved control method is presented in this paper based on modeling and analysis of dynamics. In this method, a main control law is approximated by an adaptive fuzzy logic system directly, and a stable compensation taw is introduced based on a saturation function. The simulation results with complete 3-axis model illustrate the effectiveness.