高超声速滑翔飞行器再入拉起段弹道优化设计  

Trajectory Optimization on Reentry and Pull-up Phase of Hypersonic Glide Vehicle

作　　者：黄春华[1] 刘凌宇 梁彦刚[1] 

机构地区：[1]国防科学技术大学航天科学与工程学院,长沙410073 [2]北京宇航系统工程研究所,北京100076

出　　处：《战术导弹技术》2016年第1期23-27,共5页Tactical Missile Technology

基　　金：国家重点基础研究发展计划资助(2013CB733100)

摘　　要：针对高超声速滑翔飞行器"跳跃滑翔"飞行时再入拉起段高度跨度大、大气密度变化剧烈的恶劣环境,提出基于高斯伪谱法的高超声速滑翔飞行器再入拉起段弹道规划方法。首先建立高超声速飞行器动力学模型,确立约束条件,然后选取驻点热流最小为目标函数,并根据再入拉起段环境将弹道分成两段,采用高斯伪谱法建立连接条件并分段优化。结果表明,该方法计算速度快,拟合的弹道满足各种约束,并且控制量变化平缓,实际飞行中容易实现。As the altitude and density of atmosphere change quickly in reentry and pull-up phase, a method of trajectory planning based on Gauss pseudo-spectral is proposed. Firstly, the dynamic model is built, as well as the restrains. Then, the minimum of heat flow is chosen as the objective function. A strategy of partition optimization is designed. The linkage has been set by Gauss suhs show that, the method calculates quickly and satisfies all the restrictions, pseudo-spectral. The re- and the control variable changes slowly and meets the demand of actual flight.

关 键 词：高超声速滑翔飞行器 弹道规划 分段优化 高斯伪谱法 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]