摘要
针对高超声速条件下变形技术的应用模式,对具有伸缩翼的组合式飞行器滑翔弹道进行了多目标优化研究。介绍了伸缩翼的变形模式,给出了不同变形状态下的气动特性;建立了三自由度滑翔轨迹动力学模型和伸缩翼前缘热流计算模型;采用MOEA/D多目标优化算法,以变形条件和飞行攻角为设计变量、以最大射程和最小翼前缘总吸热量为目标函数,进行了多目标优化计算。优化结果表明,MOEA/D计算得到了相对均匀分布的Pareto最优解集,将伸缩翼外形与无变形外形相比,飞行器滑翔段射程得到了显著提高,同时伸缩翼前缘总吸热量有明显的降低。
In order to explore the application of morphing technology in hypersonic aircraft,a hypersonic morphing aircraft based on telescopic wing was proposed.Then the trajectory of glide phase was optimized through multi-objective optimization method.Firstly,the aerodynamic characteristics of different telescopic morphing phases were offered,the 3-degree of freedom dynamic model of free glide phase and the heat flux model of the leading edge of the wing were built.In the MOP(multi-objective optimization problem),the two optimization objectives were the range of trajectory,and the total heat of the leading edge of the wing.The optimization variables include the Mach numbers when the aircraft was morphing,and the angle of attack of different phases.MOP was solved by using the MOEA/D(multi-objective evolutionary algorithm based on decomposition).Numerical simulation results show that the proposed method can obtain the Pareto Front.Also,compared with the non-morphing aircraft,the aircraft can achieve a larger range and a smaller total heat of the leading edge of the wing.
作者
彭悟宇
杨涛
王常悦
丰志伟
涂建秋
PENG Wuyu;YANG Tao;WANG Changyue;FENG Zhiwei;TU Jianqiu(College of Aeronautics and Astronautics,National University of Defense Technology,Changsha 410073,China;China Academy of Launch Vehicle Technology,Beijing 100076,China)
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2019年第1期41-47,共7页
Journal of National University of Defense Technology
基金
国家自然科学基金资助项目(11772353)
关键词
变形飞行器
高超声速
伸缩翼
轨迹优化
多目标优化
morphing aircraft
hypersonic
telescopic wing
trajectory optimization
multi-objective optimization
