助推-滑翔式导弹中段弹道方案的初步分析

建立了助推—滑翔式弹道中段的无量纲运动方程。采用非线性规划方法实现弹道优化。首先求解不同初始速度、速度倾角和最大升阻比的最大射程弹道,然后考虑驻点热流、过载约束,求解总气动加热最小和射程最大的最优弹道。基于前者的计算结果分析了初始条件对最大射程弹道的影响。将考虑约束的再入滑翔弹道与弹道式再入的特征参数比较,表明再入滑翔弹道的峰值热流较小,而总气动加热增加,但再入滑翔飞行时间在一般锥形体再入机动飞行器的热防护系统可承受的时间范围内。

Schematic Study of Mid-course Trajectories for the Boost-glide Missiles

The dimensionless equations of motion for mid-course of the boost-glide trajectory are presented and the trajectory optimization problems are solved with nonlinear programming method(NLP).Firstly,the maximum range trajectories with varied initial velocity,inclination of the velocity and maximum lift-to-drag ratio of the vehicle were generated.Then the minimal accumulated heating load and the maximum range trajectories with stagnation heating rate and load factor constraints were investigated.The numerical results of first kind trajectories show the influence of initial condition on the maximum range trajectories.The second kind of the optimal glide trajectory was compared with the pure ballistic trajectory under the same condition.The results show that the maximum heating rate of glide reentry declines while the heat load of the glide trajectory increases.Furthermore,the flight time of the glide is within the tolerance of the Thermo Protection System(TPS) of conical shape maneuver reentry vehicles.