Two-component variable-thrust rotary detonation rocket engine based on pintle injector

Abstract

The invention discloses a two-component variable-thrust rotary detonation rocket engine based on a pintle injector. The two-component variable-thrust rotary detonation rocket engine based on the pintle injector comprises the pintle injector, a rotary detonation combustion chamber and an exhaust nozzle which are sequentially and coaxially arranged in the axial direction; the pintle injector comprises a center rod inner nozzle, a nozzle adjusting body and an injector shell which are sequentially and coaxially arranged from inside to outside in a sleeving mode; a fuel injection runner is arranged in the center of the center rod inner nozzle, a plurality of fuel injection openings are formed in the head of the center rod inner nozzle in the circumferential direction, and a broken-line-shaped oxidizing agent runner is formed between the outer wall face of the inner side of the nozzle adjusting body and the inner wall face of the injector shell; and the nozzle adjusting body can slide in the axial direction, and therefore the injection area of the fuel injection openings and the sectional area of the oxidizing agent runner are adjusted. According to the two-component variable-thrust rotary detonation rocket engine based on the pintle injector, under the condition that the equivalence ratio is not changed, the flow of a two-component propellant can be changed, thrust can be generated and changed, a fuel flowing area can be stabilized and the combustion rate of fuel can be increased by effectively utilizing a backflow area at the head of a pintle, fuel waste is reduced, and the propellant is saved.

Description

technical field [0001] The invention relates to the field of propulsion technology, in particular to a pintle injector-based dual-element variable-thrust rotary detonation rocket engine. Background technique [0002] In order to achieve the best thrust control and the precise control of the spacecraft flight, so as to maximize the carrying capacity of the spacecraft, the space engine is required to have a certain variable thrust capability. At this stage, the purpose of variable thrust is mainly achieved by controlling the injection flow rate of the propellant. There are three main injection forms commonly used in variable thrust engines: high-frequency pressure drop injectors, double-manifold injectors, and variable-area injectors, among which the pintle injector is one of the variable-area injectors. It is a variable area injector that can continuously adjust the injection area. One of the propellants is ejected from the annular gap and flows down along the outer wall of...

AI Technical Summary

Problems solved by technology

The engine combustion chamber adopts the continuous rotation detonation combustion chamber with an empty barrel structure, which has the characteristics of continuous output power and high thermal cycle efficiency, and solves the problems of unstable mixing ratio and low thermal cycle efficiency of traditional variable thrust engines.

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