Rocket ejector ramjet combustion chamber and self-adaptive fuel injection method

Abstract

The invention discloses an ejector rocket ramjet combustion chamber and a self-adaptive fuel injection method, and relates to a rocket-based combined cycle engine. The combustion chamber is composed of a rocket ejector, a temperature sensor, a fuel supporting plate and an actuating mechanism. The rocket ejector is arranged in the center of the engine; the temperature sensors are symmetrically distributed in the width direction of the combustion chamber around the central axis at certain intervals; the fuel supporting plates are annularly distributed in the combustion chamber around the central axis, the tail ends of the fuel supporting plates are connected with the actuating mechanism, and the injection angle of the fuel supporting plates is adjusted. A rich-combustion ejector rocket serves as an ignition source of secondary fuel in different working modes, the area where a rocket jet flow local high-temperature area is located is judged based on temperature sensors, the injection angle of a fuel supporting plate is adjusted, the secondary fuel injected to the bottom of the supporting plate is injected into the local high-temperature area to be rapidly combusted, and the effect of guiding flames is achieved; secondary fuel ignition and stable combustion in the downstream backflow area of the support plate are realized. The rocket injection ramjet engine works efficiently and stably in different speed domain ranges, and the thrust and specific impulse performance is improved.

Description

technical field [0001] The invention belongs to the technical field of rocket-based combined cycle engines, and in particular relates to a combustion chamber of an ejected rocket ramjet engine and an adaptive fuel injection method. Background technique [0002] Horizontal take-off and landing, reusability and single-stage entry into orbit are the long-term goals of space transportation. It is hoped to build a space transport vehicle that can take off flexibly like an airplane and have the ability to take off and land in rapid succession, so as to reduce launch preparation time and reduce launch costs. cost. Aiming at this characteristic, the concept of Rocket Based Combined Cycle (RBCC) engine is proposed. The rocket-based combined cycle engine organically combines a rocket with a high thrust-to-weight ratio and an air-breathing engine with a high specific impulse to give full play to the advantages of the two propulsion methods, and achieve good performance under a wide fl...

AI Technical Summary

Problems solved by technology

However, its complex structure increases the difficulty of control, and at the same time, numerous adjustment mechanisms will increase the weight of the engine

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