Electric ignition green unit liquid propellant rocket engine structure

Abstract

The invention provides an electric ignition green unit liquid propellant rocket engine structure. The electric ignition green unit liquid propellant rocket engine structure comprises an electrode, aninjector and a combustion chamber. The electrode is connected with the injector. A propellant is fed into the injector. A cathode and an anode of the electrode are powered on to ignite the propellant.The combustion chamber communicates with the injector. The combustion chamber is internally provided with a hot bed. The ignited propellant continues burning on the hot bed. Through the electric ignition green unit liquid propellant rocket engine structure, the defect that the self-maintaining burning capability of the electrically ignited high-performance propellant is poor is overcome, and steady-state operation of an engine can be realized. The electric ignition green unit liquid propellant rocket engine structure can be applied to a high-thrust green unit engine and is suitable for aircrafts such as satellites and carrier rockets with limited electric power.

Description

technical field [0001] The invention relates to the field of unitary liquid rocket engines, in particular to an electric ignition green unitary liquid rocket engine structure. Background technique [0002] In recent years, with the continuous progress of society and the continuous development of aerospace technology, the requirements for environmental protection and personnel health maintenance have become more stringent. It has become a trend to develop new non-toxic propulsion systems to replace highly toxic hydrazine unit propulsion systems. Aerospace powers are actively carrying out research on green unit engines and their propulsion systems. [0003] The development of new green unit propulsion technology is divided into two steps: the first generation of green unit propulsion system mainly develops a new unit propulsion system with medium specific impulse performance, which replaces the conventional toxic unit propulsion system, and realizes the non-toxic attitude cont...

AI Technical Summary

Problems solved by technology

[0005] Due to the low burning rate of some HAN-based propellants, the engine cannot self-sustain combustion after electric ignition, and the electric ignition engine can only perform pulse work according to the pulse frequency of the igniter, and cannot achieve long-term steady-state work. Therefore, it is necessary to design a new electric ignition engine The scheme ensures the steady-state operation of the engine

[0006] At present, there is no description or report of similar technology of the present invention found in China, and similar data at home and abroad have not been collected yet.

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