Aircraft supersonic air inlet channel with variable deflation system

Abstract

The invention provides an aircraft supersonic air inlet channel with a variable deflation system. The aircraft supersonic air inlet channel with the variable deflation system comprises a supersonic front body compression surface, an air inlet channel lip cover, an air inlet channel side plate, an inner plate which extends inwards from the supersonic front body compression surface; a deflation chamber, a multi-seam or porous cover plate, a deflation chamber partition plate and flow limiting openings are arranged in the inner plate, wherein the multi-seam or porous cover plate covers the deflation chamber; the deflation chamber partition plate is positioned in the deflation chamber; the flow limiting openings are formed in the lower surface of the deflation chamber; the deflation chamber is partitioned into independent sub-chambers by the deflation chamber partition plate. The size of each sub-chamber, the number of the seams/pores of the multi-seam or porous cover plate corresponding to each sub-chamber and the opening and the closing of the flow limiting openings are adjusted by moving the deflation partition chamber according to the working Mach number and the attitude angle change of the supersonic air inlet channel, so that the deflation characteristics interfered by a lip cover shock wave/boundary layer are adjusted; therefore a good boundary layer control effect can be achieved in a wider work envelope range; the air emission amount is saved; a deflation flow channel in a certain area can even be closed when necessary.

Description

technical field [0001] The invention relates to the field of aircraft design, in particular to an aircraft supersonic air inlet. Background technique [0002] The supersonic inlet is one of the important aerodynamic components of high-speed aerospace vehicles. Many functions, such as downstream disturbance isolation, have a direct impact on the working efficiency and working envelope of the propulsion system. At the same time, the supersonic inlet is still at the interface between the propulsion system and the aircraft, so it also has a significant impact on the aerodynamic characteristics, structural weight, and stealth performance of the aircraft. According to analysis, for conventional aero turbine engines (the flight Mach number is generally below 2.0), every 1% increase in the total pressure recovery coefficient of the inlet port can increase its thrust by 1.5%, and the unit fuel consumption rate will decrease by 2.5%, while for More than 50% of the total thrust of a ...

AI Technical Summary

Problems solved by technology

However, for a supersonic inlet operating in a wide Mach number range, there may be multiple shock wave / boundary layer interference phenomena in the channel, and the position and intensity of the interference area will change with the change of the flight Mach number and flight attitude angle. will also change accordingly, making it difficult for existing boundary layer outgassing controls to effectively deal with

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