一种定几何高超声速进气道自适应泄压控制概念与试验验证

Concept and experimental validation of adaptive pressure relief control for fixed geometry hypersonic inlets

为满足定几何高超声速进气道宽马赫数范围工作要求,提出了一种在进气道内压段布置敞开式自适应泄压槽的自适应泄压控制新概念,并利用数值仿真与风洞试验手段对一种内收缩比高达2.57、采用自适应泄压控制的高性能二元进气道Ma4下的自起动性能及其他不同工况下的总体性能进行了研究。结果表明,采用自适应泄压控制的高超进气道阻力小、接力点起动性能好、宽马赫数范围气动性能优越;正常工作状态下,通过自适应泄压槽的泄漏量小,高马赫数下几乎可实现气动自封闭。此外,风洞试验表明,自适应泄压槽还能显著提高进气道极限抗反压能力。

For the fixed geometric inlet operating in a large Mach number rang,a concept of adaptive pressure relief control was proposed to improve the performance.A hypersonic inlet with 2.57 internal con-tractive ratio controlled by the new technology was studied by numerical simulation and wind tunnel test. The results showed that the inlet had the lower drag,better general and self-starting performance.And this slot design had little outgassing rate,even self-closed under higher Mach number.At the same time,the wind tunnel test result affirmed that the limit back-pressure capability was improved.