Small-scale two-stage rocket combination ramjet

Abstract

The invention provides a small-scale two-stage rocket combination ramjet. The small-scale two-stage rocket combination ramjet comprises an air inlet channel, an isolation section, a first-stage combustion chamber, a second-stage combustion chamber, a tail spraying pipe, a first rocket unit, a fuel injection hole and a second rocket unit. The air inlet channel, the isolation section, the first-stage combustion chamber, the second-stage combustion chamber and the tail spraying pipe are sequentially connected. Airflow flows in through the air inlet channel, passes through the isolation section, the first-stage combustion chamber and the second-stage combustion chamber and then is exhausted outwards through the tail spraying pipe. The air inlet channel provides needed capture air for an RBCC engine through profile changes under different flight Mach numbers and work modes. The isolation section is used for stably isolating the air inlet channel from the first-stage combustion chamber and used for containing pre-combustion shock train formed under the pressure action of the combustion chambers, the situation that the airflow fluctuates greatly at the air inlet section, and consequentlythe combustion efficiency is influenced is avoided, and the matching stability of the air inlet channel and the rocket unit is improved.

Description

technical field [0001] The invention relates to the field of air-breathing combined propulsion systems, in particular to a small-scale two-stage rocket combined ramjet. Background technique [0002] The Rocket-Based Combined Cycle (RBCC) 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, subcombustion, and scramjet And pure rocket 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 Mach number range, as well as smooth transition between different modes, is the key to the success of the RBCC engine. Among them, the configuration and working method adopted by the RBCC engine play a decisive role. In particular, how to ensure a reasonable match between the rocket layout and the ramjet runner layout is the key t...

AI Technical Summary

Problems solved by technology

[0003] At present, the commonly used RBCC engine structure scheme is "variable geometry inlet + middle / side rocket or liquid fuel injection + fixed geometry second-stage combustion chamber + variable geometry tail nozzle". For an RBCC engine with an area less than 0.1m2, if the built-in rocket is arranged at the front end of the engine, when it works in a state of large flow and high chamber pressure to contribute to the main thrust of the engine, it will seriously affect the starting ability of the inlet in the ejection mode, and in the When the flight Mach number is low, it is more difficult to generate thermal congestion in the combustion chamber; and if the built-in rocket is arranged at the tail of the engine, it can play a role in boosting, but the air ejection and suction capacity provided in the ejection mode will be reduced. Big discount

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