摘要
研究了气动力/推力矢量复合控制导弹发生故障后的直接自修复飞行控制系统设计问题。结合舵面的功能冗余及推力发动机推力冗余对导弹的结构故障进行功能重构,在控制律重构的过程中不需要知道确切的故障信息。自修复过程采用模型跟随的方法,在保持基本控制律不变的前提下,利用实际模型和参考模型的状态误差构造自修复输入向量。得到的自修复控制律适用于导弹的各种结构性故障(舵面卡死、缺损、浮松等)。以导弹发生左升降舵卡死故障为例,严格证明了该自修复控制律对导弹升降舵卡死故障的修复能力,最后通过仿真验证了该直接自修复控制律的有效性。
In this paper, a design and implementation of the directional reeonfigurable control system for control surfaces faults compensation is presented in the presence of faults for missile with aerodynamic force/thrust vector control. Because the missile has the functional redundant of control surfaces and thrust forces of engines, it is impossible to process the reconfigurable control law for the structural faults of missiles, and an accurate information of faults did not need. The proposed directional reconfigurable control system used the method of model following, and the resulting control system was implemented in a retrofit fashion, i.e. the baseline controller was retained, and self-repairing control inputs vector was implemented by using the state errors of actual model and reference model. The resulting reconfigurable controller has the capability of accommodating a majority of the structural faults for missiles （surface stuck, damages, floats, etc）. For instance, the reconfigurable control law for a stuck fault is proved mathematically to be practical and the effectiveness of the proposed control law is demonstrated in simulations.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2008年第6期1901-1907,共7页
Journal of Astronautics
关键词
导弹
推力矢量
自修复控制
卡死故障
Missile
Thrust vector control
Reconfigurable control
Stuck fault
