A rectangular inlet binary hypersonic variable geometry inlet, its design method and working method

Abstract

The invention discloses a binary hypersonic-velocity variable-geometry air inlet way with a rectangular inlet, a design method thereof and a working method thereof, and is applied to an air breathing type hypersonic flight vehicle propelling system. A part adjustable top plate capable of partially rotating is designed and mounted based on a traditional hypersonic-velocity air inlet way structure with a rectangular section; the position of the part adjustable top plate is adjusted according to flying conditions of a flight vehicle; the part adjustable top plate rotates by a small angle to form front and back two flow leakage windows; a front edge is designed near the section of the inlet; and a back edge is designed in the connected place of the part adjustable top plate and a throat way. A boundary layer developed from a part precursor or a large separation package formed by not starting is discharged by using simple rotation; and the starting capacity of the air inlet way is improved through the flow leakage of the throat way. The starting performance of the air inlet way can be prominently improved by only two times of rotating adjustments of the air inlet way in the starting acceleration process. The small-angle rotation variable-geometry process is easier to realize; the restarting control timeliness is better; the flowing control to the air inlet way is more comprehensive; and the pneumatic performance of the air inlet way is comprehensively improved.

Description

Technical field: [0001] The invention relates to a rectangular inlet binary hypersonic variable-geometry inlet, a design method and a working method thereof, which belong to the field of aerodynamic design of aerospace vehicles. Background technique: [0002] For an air-breathing hypersonic vehicle using a scramjet propulsion system, it is very important for the vehicle that the intake port is in the activated state. Existing foreign flight tests, such as the flight tests of X-43A and X-51A, all failed due to the failure of the inlet port to start. The start-up performance of the inlet port determines the overall performance of the aircraft to a large extent. . In particular, for a hypersonic vehicle operating in a wide Mach number range, when it is in a non-design working state, the inlet can start normally with less resistance and flow loss, and provide enough airflow for the engine to meet certain airflow quality requirements. The air flow rate is an important criterion...

AI Technical Summary

Problems solved by technology

However, due to the integrated design of the binary configuration at this time, the precursor develops a thicker boundary layer at a low Mach number, which further restricts the starting performance of the inlet.

The three schemes respectively adopt the front / rear sweep side plate and the discharge flow to improve the starting performance of the intake port, but correspondingly sacrifice the ability to capture the flow

Although the existing variable geometry scheme can improve the starting performance of the intake port, there is a limitation in timeliness when restarting

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