多约束下助推滑翔弹道发射角优化研究

Optimization of Launching Angle for Multi-constrained Aid-gliding Trajectory

临近空间飞行器利用临近空间独特的环境特点,采用助推滑翔式弹道实现高超声速滑翔和机动,极具发展潜力,但同时对助推段与滑翔段交班条件、恶劣环境下的精确末制导等方面提出了极为苛刻的要求,因此助推段飞行程序的设计对全弹道而言至关重要。针对临近空间飞行器基于助推滑翔式弹道打击不同距离目标的要求,在满足多约束条件下,采用复合形法对弹道的发射角进行优化,优化后的发射角可以有效降低后续滑翔、再入段的设计难度,为弹道设计提供较大的设计裕度。仿真结果显示,该方法有效且对初始控制参量取值要求不严格,具有较强的适应性。

In near - space unique environment, the hypersoar gliding maneuver technology based on the aid- gliding trajectory possesses a great developing potential. Meanwhile it has put forward rigorous demands on hand - over conditions between the boost and the skipping phase and precision terminal guidance. Then the flight program of the boost phase becomes very important to trajectory design. Aiming at the requirements that the multi- constrained aid- gliding trajectory can realize the different range, the launching angle is optimized by the complex method to satisfy multi - constraints. This method can provide much design margin for glide and reentry phases to reduce integral design difficulties. Simulation results illustrate the validity and the currency of this means which isn＇t sensitive to initial variables.