摘要
针对概念设计阶段需对众多外形设计方案进行比较、分析和筛选以及大量使用CFD面临的挑战,提出了可用于高超声速飞行器概念设计的快速气动设计方法。该方法运用Open VSP实现对飞行器几何外形高精度参数化建模,气动力计算使用自主开发的一种基于当地表面斜度法和参考焓法的高超声速飞行器气动特性快速工程计算工具。最后以类X-37B飞行器为例进行气动敏感度分析,表明该方法具有较高的效率和精度。
In the conceptual design stage,many candidate shapes have to be explored,studied and screened out to calculate the aerodynamic characteristics. Therefore,a rapid aerodynamic design method for the conceptual design of hypersonic air vehicles is developed and demonstrated by performing a detailed sensitivity analysis of a hypersonic air vehicle. Open VSP is used to achieve high-fidelity parametric geometry modeling and a rapid analysis tool for aerodynamics and aerothermodynamics of hypersonic vehicles is developed and validated. The method performs exceedingly,efficiently and accurately in determining the sensitivity of similar X-37 B aircraft.
作者
徐增
昂海松
李正洲
Xu Zeng Ang Haisong Li Zhengzhou(National Defense Key Laboratory of Aircraft Advanced Design Technology, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China)
出处
《战术导弹技术》
北大核心
2017年第1期1-8,共8页
Tactical Missile Technology
基金
江苏高校优势学科建设工程基金
关键词
高超声速飞行器
参数化几何建模
气动设计
工程计算
敏感度分析
hypersonic vehicle
parametric geometry modeling
aerodynamic design
engineering computation
sensitivity analysis
