临近空间“变马赫数”宽速域飞行器设计及减阻防热机理研究

The whole-speed range vehicle has the huge drag and serious aero-heating environment in the supersonic/hypersonic flows, “lift-increase, drag reduction and thermal protection” is very important for the integrated design of whole-speed range vehicle. The novel concept design for the drag reduction and thermal protection that combining “Variable Ma design method”, “Variable blunt leading edge method” and “Novel opposing jet scheme” into together is not only able to make the whole-speed range vehicle having the stable aerodynamic performance, but also can improve the aero-heating environment and the purpose of lift-increase and drag reduction. At the same time, the scheme can also improve the performance of drag reduction and thermal protection well for the whole-speed range vehicle. The mechanism that “lift-increase, drag reduction and thermal protection” for the novel concept scheme is investigated in detail by the hybrid theory analysis, LES/RANS method and experimental technique. The influences of the design and injector configuration parameters have been analyzed as well. Then, the important factors which affect the effect of drag and aero-heating reduction have been obtained. Based on the researches mentioned above, the novel concept for drag and aero-heating reduction has been optimized and explored by the multiobjective dynamical particle swarm optimization algorithm based on the Kriging surrogate model and the self-organizing mapping neural network. This is very important for the integrated design of whole-speed range vehicle.

全速域飞行器在高速段飞行过程中具有巨大的波阻和严峻的气动加热环境，“增升、减阻、防热”一体化设计对全速域飞行器的总体设计具有重要意义。将“变马赫数”宽速域乘波设计、“变钝化前缘”设计与“新型”逆向射流设计相结合的新概念减阻防热方案，不仅能够使全速域飞行器在高速段具有良好稳定的气动性能，而且能够很好地改善气动加热环境和增升、减阻效果，能够很好地提高全速域飞行器的减阻防热性能。结合理论分析、混合LES/RANS数值模拟方法和地面实验技术研究新概念减阻防热方案的“增升、减阻、防热”机理，探索设计参数和结构参数对流场波系结构与减阻防热性能的影响，分析影响减阻防热效果的关键因素。在此基础上，结合基于Kriging代理模型的多目标动态粒子群算法和自组织映射神经网络实现对新概念减阻防热方案的设计优化与数据挖掘，实现新概念减阻防热方案的多目标设计与优化，这对全速域飞行器的总体设计具有十分重要的意义。

本项目以全速域飞行器设计与其减阻防热技术为研究背景，采用理论分析和数值仿真为主要手段，在“变马赫数”宽速域飞行器设计方法、“变钝化前缘”设计与“新型”逆向射流方案相结合的基础上提出了新概念减阻防热方案，并系统研究了其减阻防热机理。.研究内容主要包括三部分：1）“变马赫数”及“变钝化前缘”宽速域飞行器设计方法研究。采用“变马赫数”宽速域乘波设计理念设计了宽速域乘波飞行器，开展了“变钝化前缘”设计方案中的钝化尺度、位置及钝化方式对全速域飞行器性能影响的研究。2）“新型”逆向射流方案的减阻防热机理研究。主要包括喷缝、多孔等“新型”逆向射流流场结构及减阻防热特性分析，研究了其与超声速自由来流之间的相互作用机理。开展了工作参数和结构参数对“新型”逆向射流减阻防热性能影响的研究。3）“变钝化前缘”与“新型”逆向射流方案相结合的优化设计及应用研究。将“新型”逆向射流方案与“变钝化前缘”设计相结合应用于宽速域飞行器，详细研究了其“增升、减阻、防热”性能，总结了不同射流方案对宽速域乘波飞行器前缘的减阻防热影响规律。研究表明“新型”逆向射流方案能够改善高超声速飞行器局部热环境恶劣的现象。同时研究成果可应用于高超声速飞行器头部设计方案中，可以通过变钝化前缘设计，实现增升减阻。也可针对高超声速飞行器控制舵设计，采用“变钝化前缘”+“多孔射流”组合方案，能够有效解决空气舵前缘热环境恶劣的情况，同时降低舵面阻力。针对未来高超声速飞机设计，机翼前缘同样可以采用本项目的研究成果来实现增升、减阻及防热目的。经过本项目的研究，对高超声速飞行器的工程型号研制有一定的指导意义，将理论研究与工程实现相结合，具有较强的应用价值，同时在国防领域也有潜在的应用方向。