一种吸气式高超声速缩比模型设计方法

如有对接意向，请电话垂询010-68918340

一种吸气式高超声速缩比模型设计方法

本发明涉及一种吸气式高超声速缩比模型设计方法，包括一、计算全尺寸模型隔离段边界层厚度d0；二、计算缩比模型隔离段边界层厚度d1；三、缩比模型隔离段高度h1＝R*(h0-d0)+d1；四、计算流量调节片理论高度d；五、计算流量调节片最大厚度Dmax＝d*c，c＝1.5～3；六、流量调节片高度变化范围为d～dmax；其下表面为平面，安装在进气道底座上；其前端与进气道压缩面的斜度一致；隔离段部分是等高的，在燃烧室部分的上表面与实际飞行器燃烧室的流道几何相似。本发明提高缩比模型测力试验时进气道的起动性能和内阻测量精度，使缩比模型的测力实验结果和高超声速飞行器的实际性能一致。

Design method of aspiration hypersonic velocity scaling model

The invention relates to a design method of an aspiration hypersonic velocity scaling model. The design method comprises the steps that firstly, the thickness d0 of a boundary layer of a separation section of a full scale model is calculated; secondly, the thickness d1 of a boundary layer of a separation section of a scaling model is calculated; thirdly, the height h1 of the separation section of the scaling model is equal to R*(h0-d0)+d1; fourthly, the theoretical height d of a flow regulation sheet is calculated; fifthly, the maximum thickness Dmax of the flow regulation sheet is equal to d*c, specifically, c is equal to 1.5-3; and sixthly, the height variation range of the flow regulation sheet is d-Dmax. The lower surface of the aspiration hypersonic velocity scaling model is a plane, and is mounted on a base of an air inlet channel. The front end of the aspiration hypersonic velocity scaling model is the same as the compression surface of the air inlet channel in gradient. The separation sections have the equal altitude, and the upper surface of a combustion chamber is geometrically similar to a flow channel of an actual flight combustion chamber. According to the design method, the starting performance and internal resistance measurement precision of the air inlet channel are improved during the force measuring test of the scaling model, and the force measuring test result of the scaling model and the actual performance of a hypersonic velocity flight are consistent.