Simultaneous lateral thrust and aerodynamic control of an agile missile
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摘要: 讨论了敏捷导弹的气动力与姿控发动机侧向推力复合控制.提出将控制系统分成控制律和复合逻辑两部分进行设计的方法,对敏捷导弹进行复合控制,并通过具体的仿真实例比较了在纯气动控制以及姿控发动机在连续和脉冲形式下的控制效果.最后分析了姿控发动机到拦截器质心的距离对控制效果的影响.Abstract: The blended control of a tail-controlled agile missile with attitude control motors is discussed. A controller, including aerodynamic control surface and pulse type lateral jets, was developed. It was divided into two parts: the control law and the blend logic. The control law can be designed easily as before, and the blend logic commands the two actuators. Simulations had been carried out to show the performance. Effect of the distance between motors and the center of gravity of the interceptor had been also discussed.
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Key words:
- guided missile control /
- impulse control /
- rocket thrust /
- blended control /
- attitude control
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[1] Chadwick W R. Augmentation of high-altitude maneuver performance of atail-controlled missile using lateral thrust . ADA328973, Virginia:Naval Surface Warfare Center, 1995 [2]Herman R, Bulter J. Subsystems for the extended range interceptor (ERINT-1) missile . AIAA92-2750, Dallas:LTV Aerospace and Defense Co, 1992 [3]O'Reilly P, Walters E. Patriot PAC-3 missile program-an affordable integration approach . ADA319957, Dallas:Lockheed Martin Vought Systems Corp, 1996 [4]Menon P K, Iragavarapu V R. Adaptive techniques for multiple actuator blending . AIAA98-4494, Boston:AIAA, 1998 [5]Reichert R T. Dynamic scheduling of modern robust control autopilot designs for missiles[J]. IEEE Control System Magazine, 1992, 12(5):35~42 -
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