Axisymmetric internal parallel type bimodal air inlet channel for RBCC engine and control method thereof

Abstract

The invention discloses an axisymmetric internal parallel type bimodal air inlet channel for an RBCC engine and a control method thereof. The air inlet channel comprises a center body, a lip cover, a stretchable tail cone, a flow dividing partition plate and an actuating component; an ejection channel is formed in the flow dividing partition plate; and a high-speed stamping channel is formed between the flow dividing partition plate and the lip cover. When the speed is low, the stretchable tail cone is pushed to the forefront, and at the moment, the ejection channel is completely opened; when the speed is high, the stretchable tail cone is pushed to the rearmost position, at the moment, the rocket ejection channel is completely closed, and the high-speed stamping channel works independently; and therefore, the aerodynamic performance of the air inlet channel at high speed and low speed is considered, the combined engine can effectively work in a wide flight envelope, and the air inlet channel has the advantages of being small in windward area, compact in layout, large in internal available volume ratio and the like.

Description

technical field [0001] The invention relates to the field of aircraft design, in particular to an axisymmetric internal parallel air intake that can be used for RBCC engines. Background technique [0002] The rocket-based combined cycle (Rocket Based Combined Cycle, hereinafter referred to as RBCC) engine organically combines the rocket engine and the ramjet engine. Compared with the traditional Compared with the engine, RBCC can start from zero speed and has a larger thrust-to-weight ratio, so it can meet the needs of the aircraft's high-thrust acceleration, high-efficiency cruise, and full-airspace and full-speed flight at the same time. As an important part of the RBCC engine propulsion system, the intake port not only needs to efficiently provide air with a certain pressure, temperature and flow rate to the engine within a wide range of Mach numbers, but also shoulders the task of working mode conversion and outlet flow field uniformity adjustment. And functions such as...

AI Technical Summary

Problems solved by technology

However, in the case of using a three-dimensional axisymmetric inlet port, it is difficult for the designer to arrange a rotatable splitter plate like the above-mentioned binary RBCC inlet port, which means that once the axisymmetric inlet port configuration is adopted, it is difficult for the designer to Arrange the rocket channel and the stamping channel in parallel, but have to adopt a series layout scheme

However, the tandem RBCC inlet is difficult to protect the turbine module when flying at a high Mach number, and the turbine module will cause a large flow loss when flying at high speed, thus affecting the overall performance of the engine at a high Mach number

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