Unidirection control combined power adjustable air inlet way and design method thereof

Abstract

The invention discloses a unidirection control combined power adjustable air inlet way and a design method thereof. The air inlet way is composed of a first-stage bending compression face, a second-stage bending compression face, a fixing lip cover, a throat equal straight section and a square-to-round expansion section. The unidirection control combined power adjustable air inlet way is characterized in that a hook face+wedge face combined external pressure section wave system combinatorial arrangement is provided and is applied to a binary supersonic velocity air inlet way external pressuresection top plate rotating variable geometry scheme, it is guaranteed that the combined power adjustable air inlet way can normally work under all mach numbers, meanwhile, the contradiction that consideration cannot be given to supersonic velocity air inlet way low mach starting capacity and high mach number aerodynamic performance is avoided. The adjustable second-stage compression face is a unique motion component of the overall air inlet way, and one motor is used for achieving unidirection control over two geometrical parameters including air inlet way second-stage compression angles and the throat height.

Description

Technical field [0001] The invention relates to a single-degree-of-freedom control combined power adjustable air inlet and a design method thereof, belonging to the technical field of combined power air inlet design. Background technique [0002] The air-breathing hypersonic propulsion technology has become one of the current research hotspots in the international aerospace industry. As the key aerodynamic component of the air-breathing hypersonic propulsion system, the design form and working characteristics of the air inlet directly affect the overall effectiveness of the propulsion system. However, the excellent aerodynamic performance of the intake port in the design state cannot guarantee that it can work normally and stably under all critical working conditions. The contradiction between the starting ability under low Mach number and performance under high Hz has become a constraint A prominent problem in wide-speed range flight is that conventional fixed geometry inlets ca...

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Problems solved by technology

[0004] In addition, according to the form of the compression surface of the external pressure section, the binary supersonic inlet is divided into a conventional multi-stage wedge surface compression inlet and a curved surface compression inlet. Deceleration and supercharging, this type of binary inlet wave system has a simple structure and a short design cycle, including the X-43A and X-51A in the United States and the Hyshot in Australia, which mostly use conventional two-stage or three-stage external compression. The compression efficiency of the wave system is average, the length of the external pressure section is long, but the degree of flexibility is high, and each rotating plate in the external pressure section can rotate around the fixed hinge, but the adjustment process often requires multi-degree-of-freedom adjustment (under different incoming flow Mach numbers, often Need to adjust the multi-stage rotating plate), the design of the adjustment mechanism is relatively difficult; while the latter realizes the deceleration and boosting of the airflow through a bending shock wave, the compression efficiency is high, and its design is relatively complicated, and the design method mostly adopts the characteristic line method for forward Or reverse design, but since there is no two-stage rotatable compression surface for single curved surface compression, if the top plate is rotated and adjusted geometrically, the airflow will go through the process of compression-expansion-recompression, which is not good for the performance improvement of the intake port

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