基于hp-RPM的高超声速飞行器滑翔轨迹优化  

Hypersonic Flight Vehicle Glide Trajectory Optimization Based on hp-RPM

作　　者：田敏杰 李伟[1] 李世珍[1] Tian Minjie;Li Wei;Li Shizhen(Beijing Electro-Mechanical Engineering Institute,Beijing 100074,China)

机构地区：[1]北京机电工程研究所,北京100074

出　　处：《战术导弹技术》2020年第5期76-84,148,共10页Tactical Missile Technology

摘　　要：针对高超声速飞行器再入滑翔段不同目标函数下的轨迹优化问题,采用hp自适应Radau伪谱法(hpRPM)得到了满足热流密度、过载和动压等过程约束条件,以及指定飞行状态和位置的终端约束条件下的最大纵程、最大横程、最小飞行时间和绕飞航迹,并预估了飞行器的滑翔可达区域。发现地球自转对滑翔射程有较大影响,顺地球自转方向飞行可延长滑翔时间;跳跃式滑翔比拟平衡滑翔可增大射程,但也带来了更加严重的过程约束问题。该方法可为结构热防护和制导控制系统提供可行的规划轨迹,具有一定的工程应用价值。Aiming at the reentry glide trajectory optimization problem under different objective functions of the hypersonic aircraft,the hp-adaptive Radau pseudospectral method( hp-RPM) is used to obtain the maximum longitudinal range,maximum horizontal range,minimum flight time,trajectory and the gliding reachable area,under the process constraints such as heat flow density,overload and dynamic pressure,as well as the terminal constraints of the specified flight state and position. It discovered that the rotation of the earth has a great impact on the glide range,which means flying in the direction of rotation of the earth can extend the gliding time. The jumping gliding can increase the range compared to balanced gliding,but it also brings the problem of more severe process constraints. This method can provide a feasible planning trajectory for structural thermal protection and guidance control systems,and has certain engineering application value.

关 键 词：伪谱法 高超声速飞行器 轨迹优化 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]