一种临近空间高升阻比滑翔飞行器概念设计

Concept design of a near-space high L/D ratio glide vehicle

以常规临近空间滑翔飞行器为背景,完成了一种新的临近空间高升阻比滑翔飞行器的气动布局概念设计。首先简要介绍了飞行器的布局形式和操纵舵面配置方式,初步确定了飞行器的基本总体参数;再利用气动力快速计算方法完成了飞行器气动力的计算;在此基础上,详细分析了其纵向和横侧向稳定性与操纵特性;最后,完成了飞行器3 000 km常规射程的滑翔弹道设计和仿真。仿真结果表明,所设计的临近空间高升阻比滑翔飞行器满足热流、动压等多种约束要求,具有一定的工程应用价值。

Based on the application of near-space,this paper designs a new concept conventional high L/D ratio near-space glide vehicle. The vehicle＇s control surfaces are distributed,and the basic parameters are initially determined. Then,the vehicle＇s aerodynamics are computed by a rapid computing software. With these aero data,the longitudinal stability and lateral control characteristics are analyzed in detail. Finally,a 3 000 km glide trajectory are designed for this vehicle. Simulation results show that this vehicle meets the requirements for heat flux and dynamic pressure constrains,which has certain value for engineering application.