高超声速飞行器改进阻力加速度剖面设计  

Improved Drag Acceleration Profile Design for Hypersonic Vehicles

作　　者：王哲浩 李田 闫海冬 胡玉东 高长生[1] WANG Zhehao;LI Tian;YAN Haidong;HU Yudong;GAO Changsheng(School of Astronautics,Harbin Institute of Technology,Harbin 150001,China;Beijing Institute of Electronic System Engineering,Beijing 100854,China)

机构地区：[1]哈尔滨工业大学航天学院,黑龙江哈尔滨150001 [2]北京电子工程总体研究所,北京100854

出　　处：《现代防御技术》2024年第2期115-123,共9页Modern Defence Technology

摘　　要：针对高超声速飞行器在滑翔段标称轨迹制导过程中的阻力加速度剖面设计问题,提出了一种改进的阻力加速度剖面设计方法。为增大飞行器滑翔段航程,改善飞行状态参数,设计了以能量倒数为自变量的二次函数形式剖面,通过改变剖面中点处阻力加速度值的方式对剖面形状进行调整,以满足高超声速飞行器各项约束。仿真结果表明,与传统二次函数阻力加速度剖面进行对比,该阻力加速度剖面能够增加最大滑翔距离,并改善飞行状态参数,能支持飞行器完成禁飞区绕飞任务。To address the drag acceleration profile design challenge during the gliding trajectory guidance of hypersonic vehicles,this paper proposes an improved method for designing the drag acceleration profile.To enhance the gliding range of the aircraft and improve flight state parameters,the paper designs a novel drag acceleration profile in the form of a quadratic function with the reciprocal of energy as the independent variable.The profile shape is adjusted by changing the drag acceleration values at the midpoint,satisfying various constraints of hypersonic flight.Simulation results indicate that,in comparison to the traditional quadratic drag acceleration profile,the proposed profile significantly increases the maximum gliding distance and improves flight state parameters,enabling the aircraft to complete flying missions around no-fly zones.

关 键 词：高超声速飞行器 标称轨迹制导 滑翔段 轨迹规划 阻力加速度剖面 过程约束 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]