The invention relates to a transverse pressure gradient controllable bulge air inlet channel with a specified shock wave shape, and a design method thereof. The design method comprises the following steps: (1) specifying a shock wave curve matched with a large sweepback lip in a designed section according to the requirement of a large sweepback lip, discretizing the shock wave curve into a seriesof osculating planes, calculating a compression molded line for determining the shock wave shape in each osculating plane; (2) constructing a pressure distribution rule of decreasing progressively from the middle to the two sides, and solving residual compression molded lines according to pressure distribution in different osculating planes in step (1); and (3) combining the compression molded lines of all the osculating surfaces to form a three-dimensional bulge compression molded surface so as to ensure the common control of the shock wave shape and the transverse pressure gradient. The design method can be matched with the large sweepback lip with the same stealth requirement, the transverse pressure gradient on the surface of the external compression bulge can be controlled, then the displacement capacity of the bulge to a boundary layer is improved, and a new thought is provided for design of a supersonic speed bulge air inlet channel.
本发明涉及一种指定激波形状的横向压力梯度可控鼓包进气道及设计方法,包括以下步骤:(1)根据大后掠唇口需求,在设计截面内指定与之匹配的激波曲线,将激波曲线进行离散成一系列吻切平面;并求出每张吻切平面内决定激波形状的压缩型线;(2)构造由中间向两侧递减的压力分布规律,根据步骤(1)中不同吻切平面内的压力分布,求取剩余的压缩型线;(3)将所有吻切面的压缩型线组合构成三维鼓包压缩型面,以此保证对激波形状与横向压力梯度的共同控制。本发明提出一种设计方法既能同强隐身需求的大后掠唇口匹配,又能对外压缩鼓包表面上的横向压力梯度进行控制,进而提高鼓包对附面层的排移能力,为超声速鼓包进气道设计提供新思路。
Transverse pressure gradient controllable bulge air inlet channel with specified shock wave shape, and design method thereof
指定激波形状的横向压力梯度可控鼓包进气道及设计方法
2020-08-11
Patent
Electronic Resource
Chinese
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen |
European Patent Office | 2020
|Inlet-to-inlet shock interference tests
Engineering Index Backfile | 1965
|Inlet-to-inlet shock interference tests
TIBKAT | 1965
|