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针对临近空间高超声速滑翔飞行器机动能力强、轨迹灵活多变的特点,提出了一种基于典型控制规律的高超声速滑翔飞行器轨迹预测方法。在前期先验信息的基础上,将典型控制规律下的控制参数——攻角和倾侧角建模成一阶Gauss-Markov过程,联合飞行器在半速度坐标系下的运动微分方程组成扩展的状态变量,选择飞行器的经纬高与速度大小作为无迹卡尔曼滤波的观测量并对控制参数进行滤波辨识,结合控制参数的辨识值重构其规律,进而预测飞行器的轨迹。通过仿真分析了对跳跃和非跳跃2种典型飞行轨迹的预报效果,结果表明所提方法对倾侧角不翻转的情况具有良好的预测精度。
In view of the high maneuverability and trajectory flexibility of near-space hypersonic gliding aircraft, a trajectory prediction method for hypersonic gliding aircraft based on typical control law is proposed. Based on the prior a priori information, the control parameters of typical control law - angle of attack and roll angle are modeled as first-order Gauss-Markov process. Combined with the differential equations of motion of the aircraft in the half-speed coordinate system, an extended state variable , Select the latitude and longitude of the aircraft and the velocity as the observation of unscented Kalman filter and filter the control parameters, and reconstruct its regularity with the identification of control parameters to predict the trajectory of the aircraft. The simulation results show that the proposed method has good prediction accuracy for the cases where the tilting angle is not overturned.