摘要
针对导弹直接力/气动力复合控制问题,提出了一种基于自适应滑模控制(ASMC)与模糊逻辑的自动驾驶仪设计方法。该方法将整个导弹控制系统分为气动力控制子系统(ACS)和直接力控制子系统(RCS)两部分。前者采用自适应滑模控制理论进行设计,利用其所具有的强鲁棒性优点,克服了包括参数摄动与外界扰动在内的各类不确定性因素的影响。后者通过基于规则的模糊推理来确定不同条件下直接力作用的大小,以辅助提高气动力子系统的性能。在控制系统结构确定的条件下,利用遗传算法(GA)对各参数进行优化,实现了两个子系统之间的协调工作。仿真结果表明,所提出的控制方案对机动指令具有较好的跟踪效果,适用于直接力/气动力复合控制导弹的控制系统设计。
A missile reaction-jet/aerodynamic compound control system design method based on adaptive sliding mode control （ASMC） and fuzzy logic is proposed. The scheme separates the whole control system into two parts. The aerodynamic control subsystem （ACS） is designed on ASMC theory. Because ASMC is robust to parametric perturbations and external disturbances, the performance of system can be guaranteed greatly. The fuzzy logic is used to design the reaction-jet control subsystem （RCS）. The reaction-jet thrust is adjusted by fuzzy inference rulers on different conditions, and the response speed of ACS can be improved as a result. When the structure of whole control system is fixed, genetic algorithm （GA） is used to optimize the parameters, and the coordination between RCS and ACS is realized. Simulation results show that the proposed scheme can track the maneuver command with higher precision and faster response speed than traditional ones, and it is applicable to design the autopilot of reaction-jet and aerodynamic compound control missile.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2008年第1期165-169,共5页
Acta Aeronautica et Astronautica Sinica
基金
航天创新基金资助项目
关键词
直接力/气动力复合控制
自适应滑模控制
模糊逻辑
遗传算法
reaction-jet/aerodynamic compound control
adaptive sliding mode control
fuzzy logic
genetic algorithm
