摘要
针对大型运载火箭姿态控制系统设计的一些具体问题，如弹性振动的抑制、外部干扰的补偿等，探讨了变结构自适应理论在运载火箭姿态控制系统设计中的应用方法及其可行性。对于变结构理论的应用方法，提出了不确定性边界的自适应估值算法和基于简化模型的变结构自适应控制器设计。对设计的姿态控制系统进行了仿真，并与采用古典理论设计的姿态控制系统性能进行了比较。结果表明采用变结构自适应控制理论设计运载火箭控制系统是可行的，与古典方法相比变结构自适应方法设计的姿态控制系统具有较强的鲁棒性和较高的精确度，特别是采用不确定边界自适应估算方法可以大大提高系统的稳定性。
In view of certain concrete probleme in design of attitude control system of largelaunch vehicle, such as restraint of elastic vibration and compensation of outer disturbance,application method and feasibility of variable structure system (VSS) adaptive theory in de-sign of attitude control system of launch vehicle are inuestigated .For applicattion method of VSS, adaptive estimattion algorithm for uncertain boundaryand variable structure adaptive controller based on simplified model are presented. Simulationis perforrmed for the attitude control system, the system performances are compared wish theseof the attittude control system designed by classical theory. Simulation results indicate thatadoption of variable structure adaptive control theory in the design of launch vehicle controlsystem is feasible and the attitude control system desiged by variable stucture adaptive methodhas stronger robustness and higher accurcy than thet deigned by clasical method. In par-ticular, the adaptive estimation algorithm for uncertain boundary can improve the system ro-bustness greatly.
出处
《航天控制》
CSCD
北大核心
1997年第4期9-16,共8页
Aerospace Control
