Two-dimensional variable geometry hypersonic intake port provided with rectangular inlet as well as design method and working method of two-dimensional variable geometry hypersonic intake port

Abstract

The invention discloses a two-dimensional variable geometry hypersonic intake port provided with a rectangular inlet as well as a design method and a working method of the two-dimensional variable geometry hypersonic intake port. A rotatable adjustable top board is designed and mounted on the basis of a traditional hypersonic intake port structure provided with a rectangular section, and the angle position of the adjustable top board is adjusted according to the flight condition of an aircraft; a front suction window and a rear suction window are formed through small-angle rotation of the adjustable top board, the front-edge suction window is designed on the final-stage top board front edge, and the rear-edge suction window is designed in the position where the adjustable top board and a throat are connected. A boundary layer developed by a precursor is taken out through simple rotation under the condition of low mach number in the acceleration process, a final-stage wedge angle is reduced during rotating, flow capture is improved while shock wave is weakened, further, the mach number of an inlet at an inner contraction section is relatively increased, and accordingly, the starting performance of the intake port is improved; the starting performance of the inner contraction section of the intake port is improved through throat suction; the variable geometry process adopting small-angle rotation is easier to realize, the starting performance under the condition of the low mach number is improved, the flowing control is more comprehensive, and the aerodynamic performance of the intake port 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 will develop a thicker boundary layer at low Mach numbers, which restricts the starting performance of the inlet.

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

But at this time, when the inlet works at lower than the design Mach number, due to the relatively large external pressure and the large total deflection angle, it will cause a large overflow loss, and at the same time, the shock wave loss is also relatively large

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