远程弹道式飞行器机动制导方法

Maneuver Strategy and Guidance Law of Large-range Ballistic Vehicle

以一种远程弹道式飞行器为研究对象,研究了弹道落点可以覆盖大面积区域的机动弹道设计及制导方法。采用兰伯特定理设计机动弹道,并采用迭代的方法对地球非球形摄动进行补偿。在考虑发动机性能的基础上,采用速度增益制导算法对飞行器进行关机制导。为了保证再入点的高精度要求,提出了一种弹道修正制导算法,制导过程分为横向制导和纵向制导,横向制导采取相平面法,纵向制导采用一种解析的闭路制导算法。仿真结果表明,该文方法能够使飞行器较好地实现远程机动飞行,具有较好的鲁棒性。

Taking large-range ballistic vehicle as research object,the maneuver scheme and guidance law making the fall-points of the vehicle cover a large area were studied. Lambert theory was used to design the maneuver trajectories, and the non-spherical perturbation of the earth on trajectories was compensated by iterative method. Considering the performance of engine performance, the velocity-gain guidance method was designed to determine the shut-off time of the engine. To improve the terminal precision, a correction guidance method was proposed,and the guidance process was divided into horizontal guidance and vertical guidance. The horizontal guidance is based on the phase plane while the vertical guidance is based on an analytical closed-loop guidance-law. The simulation results indicate that the proposed guidance law is effective and robust.