Double-channel variable geometry rocket base combined cycle engine

Abstract

The invention discloses a dual-channel variable-geometry rocket-based combined cycle engine, which adopts a dual-channel structure and realizes good work in a wide flight range through a partitioned combustion mode; the dual channels work simultaneously in a low-speed flight state to complete ejection mode and sub-stage The work in the low-speed section of the combustion mode; in the high-speed flight state, it is converted to the high-speed channel to work alone, and completes the work of the high-speed section of the sub-combustion mode and the super-combustion mode. The variable geometry method that the top pressure plate rotates around the rotating shaft is used to realize the adjustment of the small shrinkage ratio in the low-speed flight state and the large shrinkage ratio in the high-speed flight state, and meet the air capture and airflow compression requirements under different flight Mach numbers in a wide range of the engine. The binary mixed pressure inlet is adopted, the top pressure plate and the side plate of the inlet have good adhesion, and the mechanical dynamic seal is easy to realize, which is suitable for engineering applications; it meets the power requirements of different working modes of the aircraft. The top pressure plate and the conversion plate are respectively connected to the rotating shaft of the double fulcrum structure, the structure is rigid, and the high temperature sealing is easy to realize.

Description

technical field [0001] The invention relates to the field of air-breathing combined ramjet engines, in particular to a dual-channel variable geometry rocket-based combined cycle engine. Background technique [0002] Rocket-Based Combined Cycle RBCC (Rocket-Based Combined Cycle) engine organically integrates a rocket engine with a high thrust-to-weight ratio and an air-breathing ramjet engine with a high specific impulse in the same flow channel, and is compatible with ejection, sub-combustion, scramjet and pure rockets Mode, to achieve high-performance work in wide speed range and large airspace. How to ensure that the same engine can achieve good operation of each mode in such a wide range of Mach numbers, and the smooth transition between different modes is the key to the success of the rocket-based combined cycle engine. The configuration and working method of the rocket-based combined cycle engine play a decisive role. In particular, how to ensure that the inlet of the...

AI Technical Summary

Problems solved by technology

[0004] (1) The binary inlet adopts the variable geometry method of the lifting throat, and there must be a follow-up section between it and the combustion chamber, which will not only cause serious high-temperature dynamic sealing problems, but also limit the layout of the rocket engine. The matching between the inlet port and the rocket is poor;

[0005] (2) The flow control method of boundary layer suction is adopted in the air inlet, and additional auxiliary devices must be configured, which will bring redundant mass and additional resistance to the aircraft;

[0006] (3) The variable geometry method of lifting and lowering the top pressure plate is adopted for the side pressure air inlet, which will cause the geometric matching between the top pressure plate, the side pressure plate and the support plate to be difficult, and serious mechanical seal problems will occur.

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