偏置比例导引末制导控制

Terminal guidance control based on biased proportional navigation

在空间航天器近距离观测和故障诊断过程中,要求距离航天器足够近。从防碰撞角度出发,提出了偏置导引近距离飞跃的要求。针对此要求,在相对运动模型的基础上,根据二维平面内期望的偏置距离与视线转率之间的关系,扩展到三维空间中重新构造偏置项,推出了一种具有终端偏置距离约束的偏置比例导引律,在视线坐标系的两平面内分别应用该导引律进行偏置控制来实现垂直于视线的平面内任意方向的偏置。最后对顺轨低速和逆轨高速两种不同交会方式进行了六自由度数学仿真,仿真结果表明,两种交会方式的脱靶量误差均小于0.5 m,能成功将飞行器导引到目标近旁飞跃点,且在偏置末制导过程中稳定了飞行器的姿态,从而验证了偏置制导控制的可行性,为对目标近距离观测提供了一种新的方法。

In the process of satellite proximity observation and fault diagnosis, the vehicle was required to be close enough to the satellite. From the perspective of anti-collision, the flyby demand of biased proportional navigation was proposed. Aiming at this demand and based on relative motion model and the relationship between expected bias-distance and line of sight rate in 2-D plane, the bias term was reconstructed in 3-D space, and a biased proportional navigation guidance law with terminal bias-distance constraint was designed. The guidance law was applied to the two planes of the line-of-sight coordinate respectively to achieve the biased control and then realize the bias of random direction of the plane perpendicular to the line of sight. Finally, six-degree-of-freedom mathematical simulations are implemented for the intersection methods of along the rail with low velocity and inverse the rail with high velocity. Simulation results of the two intersection methods demonstrate that the miss distances are both less than 0.5 m, the vehicle is guided to the target＇s flyby point successfully, and the attitude is stabilized in biased terminal guidance control process. The proposed control method provides a feasible method for proximity observation at a flyby point near the target.