推力矢量控制空空导弹敏捷转弯弹道优化

Agile Turn Trajectory Optimization of Air-to-Air Missile with Thrust Vector Control

针对推力矢量控制的空空导弹敏捷转弯问题,根据推力矢量控制的特点,建立推力矢量控制力学模型;由于敏捷转弯姿态角变化范围大,为避免欧拉角导致的奇异问题,用四元数法建立导弹的六自由度运动方程。以转弯时间最短为指标,以推力角为控制量,以导弹姿态和速度方向均达到指定角度为终端约束条件,建立敏捷转弯最优控制问题模型。以某使用推力矢量控制的空空导弹敏捷转弯为例,用伪谱法求解其最短时间内完成转弯所需的推力矢量控制,得到满足约束要求的最优弹道和推力角变化规律。

Aiming at the agile turn of air-to-air missile with thrust vector control （TVC） , according to the features of TVC, a mechanical model of TVC is founded. The attitude angles vary in a wide range during agile turn, therefore it is required to establish six degree of fi＇eedom dynamics model by quatemion in order to avoid singularity caused by Euler angles. Taking the time-minimal as perfomlance index, the thrust angles as control variables, and the attitude angles and the orientation of the missile velocity as terminal constraints, the model of optimal control problem of agile turn is established. Pseudospectral meth- od is applied to solve the optimal control for agile turn of a missile with TVC, and the optimal trajectory and the changing rule of the thrust angles meeting requirements are obtained.