返回式滑翔飞行器最小航程轨迹优化方法  

Trajectory Optimization Research for Reentry Glide Vehicle with Minimum-Range Constraint

作　　者：许泽宇[1] 王洪波[1] 康永来 卜奎晨[1] 赵洪[1] Xu Ze-yu;Wang Hong-bo;Kang Yong-lai;Bu Kui-chen;Zhao Hong(China Academy of Launch Vehicle Technology, Beijing, 100076)

机构地区：[1]中国运载火箭技术研究院,北京100076

出　　处：《导弹与航天运载技术》2017年第2期12-15,19,共5页Missiles and Space Vehicles

摘　　要：针对返回式滑翔飞行器在高马赫状态下的落区和航程难以大幅度调节的问题,采用Gauss伪谱法和序列二次规划法进行轨迹优化,实现最小航程设计;提出了航程压缩比的概念,建立了动力学模型和飞行约束体系,以类CAV-H飞行器为对象进行了仿真。研究表明,低空速度消耗和空间机动有益于减小航程;在指定纵平面内可将最小航程压缩至最大航程的42%;当落区在指定航向上且飞行器可偏离纵面做机动时,飞行器可返回离轨原点;通过轨迹优化,可以调节返回式滑翔飞行器的航程从而控制其落区范围。To obtain the minimum-range for reentry glide vehicle, Gauss Pseudospectral Method and Sequence Quadratic Programming are adopted in trajectory optimization. Firstly, range-compress-ratio is defined, and the dynamic equations and the constraints are given. Optimization simulation based on the look-like CAV-H vehicle is conducted, the result showed that velocity consuming method and maneuvering method are useful to achieve minimum range. In the initial-flying-plane only, the minimum range can be compressed to 42% of the maximum range. While not only in the initial-flying-plane, the vehicle can return where it started to glide, and the minimum range can be 0. Through trajectory optimization, the range and landing place of the reentry glide vehicle can be in control.

关 键 词：最小航程 航程压缩比 约束体系 滑翔机动 轨迹优化 

分 类 号：V448.23[航空宇航科学与技术—飞行器设计]