机动弹头姿态解耦控制方法研究

对大机动弹头再入飞行段姿态稳定控制系统的设计问题进行了分析与研究。根据飞行控制要求 ,考虑了影响较大的气动力和气动力矩因素 ,建立了一个完全表征大机动情况下弹头运动的非线性动力学模型。然后采用非线性解耦控制理论设计了机动弹头的姿态控制系统。仿真结果表明 ,该方法能够保证系统良好的稳定性能。

Study on Attitude Stabilization Method of Maneuver Missile Head

The design of control system on attitude stability of maneuver re entry missile head is studied. According to the demand of flight control system, a nonlinear dynamics model with considerable aerodynamic forces and moments for a large maneuver re entry missile head is built. The attitude control system of maneuver missile head is designed by applying nonlinear decoupling control law. Simulational results are ideal.