摘要
脉冲发动机作为直接力与空气舵复合控制能有效提高导弹的快速性和末端大过载机动能力。由于脉冲发动机的喷流干扰会对复合控制系统的稳定性产生影响,在考虑脉冲发动机自身喷流因子效应以及对导弹气动干扰的情况下,把直接力喷流作用等效为弹体的气动力进行建模,并结合复合控制系统的性能指标以及稳定判据,对一类复合控制自动驾驶仪的鲁棒稳定性进行了分析,给出了直接力喷流作用下复合控制系统的满足性能要求的稳定边界。
Quick response capability and terminal maneuvering capability at high overload of the missile can be effectively improved by the Reaction-Jet/Aerodynamic composite control system.As the stability of the composite control system is disturbed by the jet of the micro-pulse engine,so the function of the reaction-jet coefficient and aerodynamic disturbance produced by the reaction-jet are considered in this paper.Based on these,the model is builded while the reaction-jet is served as the equivalent aerodynamic force,and with the performance indexes of the system and stability criterion,some kind of multicontroller of missile autopilot is analyzed in this paper,and then the stable region of the composite control system that meet the performance requirements has been worked out.
出处
《指挥控制与仿真》
2013年第5期91-94,共4页
Command Control & Simulation
关键词
直接力
气动力复合控制
导弹
等效气动力
鲁棒控制
aerodynamic/reaction-jet multi-controler
missile
equivalent aerodynamic
robust control
