助推-滑翔式弹道中段的近似解

研究了助推-滑翔式弹道中段的近似解。首先根据不同假设条件,给出以下四种情况的近似解:(1)自由飞行段的解;(2)只考虑气动力常迎角飞行段的近似解;(3)考虑引力和气动力的合成解;(4)平衡滑翔解。再由上述近似解合成助推-滑翔弹道中段的分段近似解。通过与数值解的对比,验证了近似解的合理性。研究结果可为新型助推-滑翔式飞行器在方案论证阶段时的弹道特性分析以及射程、峰值热流和过载等特征参数的估算提供依据。

Approximate Solutions of the Mid-Course Trajectories for the Boost-Glide Missiles

The approximate solutions of the mid-course trajectories for the boost-glide vehicles are investigated.Firstly,with different assumptions,four types of approximate solutions are presented:(1)free flight solutions;(2) aero-controlled flight solutions with constant angle-of-attack;(3) the composite solution of the free flight and aero-controlled flight;(4) equilibrium glide solutions.Then the approximate solutions of mid-course trajectories are obtained by the combination of these solutions.The comparison between the approximate solutions and the numerical solutions validates the efficiency of this approach.Further more,the solutions of this paper is benefit for the estimation of the characteristics of this new trajectory,such as maximum heating rate,load factor and dynamic pressure during the period of the project demonstration.