摘要
建立了考虑气动、推进、飞行轨迹、质量分析等分系统模型的高超声速飞行器总体设计模型;并基于文献参数给出了基准设计方案以及各设计参数边界;基于标准遗传算法,以最小燃料消耗为目标对基准方案进行了优化,得到了燃料消耗较小的设计方案。通过分析对比基准方案与优化方案,结果表明,在相同航程情况下,优化后的高超声速飞行器燃油消耗量较基准方案减少3.2%。
In this work,conceptual design scheme of hypersonic vehicle was constructed.In the scheme,Considering the aerodynamic force,propulsion system,trajectory and mass changing,a standard scheme and the design parameter space were given.In order to obtain a less fuel consumption scheme,multidisciplinary design optimization method based on the genetic algorithms was used to design the hypersonic vehicle.By analyzing and comparing the standard scheme and the optimized scheme,the results show that the global performance(fuel consumption)was improved by 3.2 percent.
作者
姜志杰
韩伟
李怡庆
李光昱
JIANG Zhi-jie;HAN Wei;LI Yi-qing;LI Guang-yu(National Innovation Institute of Defense Technology,Chinese Academy of Military Science,Beijing 100071,China;School of Aircraft Engineering,Nanchang Hangkong University,Nanchang 330063,China)
出处
《南昌航空大学学报（自然科学版）》
CAS
2022年第2期18-23,共6页
Journal of Nanchang Hangkong University(Natural Sciences)
基金
国家自然科学基金(12002144)。
关键词
高超声速飞行器
遗传算法
多学科优化
hypersonic vehicle
genetic algorithms
multidisciplinary design optimization
