远程火箭弹滑翔增程技术研究

Research on Gliding Extended Range in Long Rang Rocket Missile

基于火箭弹滑翔增程技术中采用的控制导弹法向过载和保持升阻比最优的2种滑翔控制方案,建立了滑翔弹道模型,分析了2种不同控制方案的约束条件,并进行了全弹道仿真,计算了不同下滑点对弹道增程的影响,为增程弹道控制方案的选择提供了依据。

Based on the rocket projectile with gliding extended range, making use of the method of controlling the normal acceleration and holding on the ratio of the lift force and the maximal drag force, the model of glider missile has been established, the constraint conditions of the two methods have been analyzed and the flight ballistic has been simulated, and furthermore, the influence on the ballistic trajectory of the different start point in flight path angle has been computed. The result shares reference value for selecting the control method in the design of gliding extended projectiles.