Supersonic blending reinforcing structure with adjustable frequency characteristic and rocket based combined cycle

Abstract

The invention provides a supersonic blending reinforcing structure with an adjustable frequency characteristic and a rocket based combined cycle. The supersonic blending reinforcing structure comprises a supersonic incoming flow baffle, supersonic incoming flow channels are arranged on both sides of the supersonic incoming flow baffle, and the two supersonic incoming flow channels are in communication with each other at the tail end of the supersonic incoming flow baffle and form a supersonic incoming flow blending zone. The supersonic incoming flow blending zone communicates with the supersonic incoming flow channels through flow guiding pipes, the flow guiding pipes comprise expansion cavities formed in the supersonic incoming flow baffle, and expansion pipes with adjustable volume are arranged in the expansion cavities. Due to a pressure difference between the two ends of the flow guiding pipes, jet flow can be formed in the supersonic incoming flow blending zone without providing an additional air source, and blending reinforcing control of the supersonic incoming flow blending zone is realized; and meanwhile, the expansion pipes are arranged in the flow guiding pipes, the jetflow ejected by flow guiding rear pipes has a certain frequency characteristic, and moreover, the volumes of the expansion pipes are adjustable, so that the frequency of the jet flow ejected by the flow guiding rear pipes is adjustable. The supersonic blending reinforcing structure with the adjustable frequency characteristic and the rocket based combined cycle are applied to the field of supersonic incoming flow blending control.

Description

technical field [0001] The invention relates to the field of supersonic flow mixing control, in particular to a supersonic mixing enhanced structure with adjustable frequency characteristics and a rocket-based combined engine. Background technique [0002] As a key process of Rocket Based Combined Cycle (RBCC), ejection plays the role of mixing rocket gas with incoming air. For RBCC, the free flow passes through the intake port and contacts the nozzle gas at the nozzle trailing edge. When the mixture of the two reaches the molecular level, a chemical reaction occurs, and the purpose of using the oxygen in the air to increase the specific impulse of the engine is achieved. However, due to the high velocity of the incoming flow, the residence time in the combustion chamber is extremely short (less than 1-3ms), how to realize the rapid and efficient mixing of gas and air is the key issue of injection, that is, to enhance the mixing effect, which determines the entire propulsion...

AI Technical Summary

Problems solved by technology

[0005] The passive control scheme based on changing the structure of the trailing edge has a simple structure and obvious control effects, but it is mainly aimed at the thin trailing edge mixed layer abstracted from practical problems. For the actual blunt trailing edge mixed layer, the partition is thicker and difficult Changing the structure of the trailing edge, while adopting a pointed trailing edge configuration is not conducive to heat protection

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