Buried gas inlet channel inner channel design method

Abstract

The invention provides a buried gas inlet channel inner channel design method. According to the present invention, according to the area along-with-distance change law, the center line along-with-distance distribution law and the characteristic variable along-with-distance change law, the radius change law of the semi-circle from the gas inlet channel inner channel inlet to the outlet, the radius change law of the round corner part of the rounded rectangle, the height change law of the rectangle of the round corner rectangle, and the width change law of the rectangle are calculated, the gas inlet channel inner channel molding surface is obtained through scanning, the gradual transition of the cross section shape from the non-circular shape to the circular shape and the gradual change of the cross section area are sufficiently considered, and the convenience and the flexibility of the gas inlet channel inner channel design are effectively improved.

Description

technical field [0001] The invention relates to the technical field of engine air intakes, in particular to a design method for an inner channel of a buried air intake. Background technique [0002] With the rapid development of aviation technology, high subsonic aircraft / UAVs with low cost, high stealth performance and high maneuverability have attracted more and more attention from countries. As an important part of the aircraft / UAV propulsion system, the performance of the air inlet directly affects the combat performance of the aircraft. Therefore, the research on the air inlet is very important. [0003] Due to its excellent stealth performance, buried air intakes are being used more and more widely in high subsonic aircraft / UAVs. The buried air intake is a special air intake that buries the inlet into the fuselage or wing without any protruding parts. Such a design can effectively reduce the radar cross-sectional area of ​​the aircraft, thereby having better stealth...

AI Technical Summary

Problems solved by technology

But in practice, the cross-section of the pneumatic S-bend designed by it is limited to track and field shape and shortened axis ellipse

In addition, from the published literature, there is no complete design method for the passage in the inlet, especially the change law of the characteristic parameters along the cross section cannot be found, so the design process of the inlet cannot be completed

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