高速飞机机翼的高低速气动力/热匹配快速设计优化研究  

The low/high speed aerodynamic/thermal fast matching design for high speed aircraft wing at wide-range mach numbers

作　　者：余婧 罗磊 陈兵 刘深深 王安龄[1] 吴晓军[1] 蒋安林 Yu Jing;Luo Lei;Chen Bing;Liu Shenshen;Wang Aning;Wu Xiaojun;Jiang Anin(Computational Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000

出　　处：《空天技术》2023年第5期11-21,共11页Aerospace Technology

基　　金：智强基金;重点实验室基金(基金号2021-JCJQ-LB-020-11);国家自然科学基金青年基金(12002361)。

摘　　要：宽速域飞行器是下一代飞行器的重点发展方向。不同速域下气动特性的协调兼顾、长时间严酷加热环境下的热安全问题,是该类飞行器设计需解决的瓶颈问题。以高速飞机作为宽域飞行器的典型代表,选取其关键部件——机翼开展了考虑力/热特性综合匹配的快速设计优化探索研究。对高速飞机机翼的高低速力/热匹配设计需求及特点进行了分析,在此基础上完成了机翼构型的参数化,明确了关键的优化设计变量及优化设计目标,建立了多点气动力及气动热设计目标下的优化模型,提出了可快速完成匹配设计的优化流程;对优化过程中涉及的快速气动力/热评估工具进行了介绍。通过仿真,对比分析了机翼优化前后的气动力/热性能,验证了所提出优化模型和优化方法的有效性。从仿真结果可以看出,快速评估工具的采用可以在保证优化效果的基础上快速获取匹配设计结果;设计目标中,高速升阻比与低速升力、高速升阻比和高速气动热间都是矛盾的需求,最终优化构型在低速升力系数上的提升空间较小,但高速升阻比的提升较明显,优化后机翼的平均热流密度有所改善,但驻点热流密度升高,由于前缘半径约束的限制,优化后的构型满足工程需求。The innovative development of high speed aircraft has attracted much attention especially for the long-duration ones with wide-range Mach number.It is a vital and dificult problem to give overall considerations for aerodynamic fore requirements at different Mach numbers as well as the heat safety demand during aircraft design.Focusing on this problem,considering the design requirement for low/high speed aerodynamic force/thermal matching,the fast optimization research on typical high speed aircraft wing is performed in this paper.Firstly,the design requirements are analyzed,the parameterization of the wing is carried out,and the corresponding design variables are specified.Then based on the aerodynamic force/thermal characteristics of the initial configuration,the design states and optimization objectives are determined.A mathematical optimization model is proposed afterwards,as well as the fast optimization flow.The corresponding prediction tools for aerodynamic force/thermal are also presented.Finally,numerical simulations are carried out to verify the efficiency of the proposed model and method.After aerodynamic force/thermal characteristic comparison of the wing configuration before and after optimization,it can be concluded that the requirements between high speed lif/drag ratio and subsonic lft coefficient,and those between high speed lift/drag ratio and high speed aerodynamic thermal are contradictory;the improvement on subsonic lift coefficients are small,but that on high speed lift/drag ration is considerable;after optimization,the average heat flow density is improved,while the heat flow density of the stagnation point is increased;due to the limitation on leading edge radius,the optimization results can satisfy the engineering demands.Furthermore,the adoption of engineering tools can quickly obtain the optimization results,while ensuring the optimization reliability.

关 键 词：机翼设计 宽速域气动特性 优化设计 高速飞机 匹配设计 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]