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Liquid oxygen and methane engine adopting plug-in type valves and control method

A plug-in, engine technology, used in machines/engines, rocket engine devices, mechanical equipment, etc., can solve problems such as complex engine structures, achieve good startup acceleration and shutdown deceleration, compact structure, and improve work reliability. Effect

Active Publication Date: 2019-04-09
SHANGHAI INST OF SPACE PROPULSION
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  • Abstract
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  • Claims
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Problems solved by technology

In addition, compared with the conventional attitude control engine using dinitrogen tetroxide / hydrazine fuel combination, the engine combined with liquid oxygen and methane and other low-temperature bicomponent non-pyrophoric propellants requires a special ignition system to achieve the ignition of the engine. The engine structure is relatively quite complicated

Method used

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  • Liquid oxygen and methane engine adopting plug-in type valves and control method
  • Liquid oxygen and methane engine adopting plug-in type valves and control method
  • Liquid oxygen and methane engine adopting plug-in type valves and control method

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Embodiment 1

[0026] Figure 1 to Figure 4 They are respectively the structural schematic diagram and the working principle diagram of the liquid oxygen and methane engines using plug-in valves provided by Embodiment 1 of the present invention. Such as Figure 1 to Figure 4 As shown, the liquid oxygen and methane engine using plug-in valves provided by the present invention includes a head body 1, an injector 2, a thrust chamber 3, a liquid oxygen solenoid valve 4, a methane solenoid valve 5 and a spark plug 6. The injector 2 is installed on the lower end surface of the head body 1 by diffusion welding, the thrust chamber 3 is installed on the lower end surface of the injector 2 by screws, the liquid oxygen solenoid valve 4 and the methane electromagnetic valve The valve 5 is inserted into the left and right sides of the head body 1 through screws respectively, and the spark plug 6 is installed on the upper part of the head body 1 through threads.

[0027] Preferably, a liquid oxygen inle...

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Abstract

The invention provides a liquid oxygen and methane engine adopting plug-in type valves and a control method. The liquid oxygen and methane engine comprises a head portion body, a jet injection device,a thrust chamber, a liquid oxygen electromagnetic valve, a methane electromagnetic valve and an ignition plug, wherein the jet injection device is installed to the lower end face of the head portionbody by diffusion welding, the thrust chamber is installed to the lower end face of the jet injection device through bolts, the liquid oxygen electromagnetic valve and the methane electromagnetic valve are installed to the left side face and the right side face of the head portion body in a plug-in type manner through the bolts correspondingly, and the ignition plug is installed to the upper portion of the head portion body through screw threads. By means of the liquid oxygen and methane engine, the problems existing in the prior art that a low-temperature attitude control engine is difficultto precool, and a low-temperature propulsive agent is prone to generating phase change inside the head portion of the engine can be solved, meanwhile, the liquid oxygen and methane engine has the advantages of being compact in structure, easy to operate and control and fast in response speed, and the use requirements for an attitude control power system can be met.

Description

technical field [0001] The invention relates to the technical field of liquid rocket engines, in particular to a liquid oxygen and methane engine using plug-in valves and a control method. Background technique [0002] High-performance, non-toxic low-temperature chemical propulsion technology has become the mainstream development direction of liquid rocket engines. Rocket engines and their propulsion systems based on the combination of liquid oxygen and methane propellants have the highest comprehensive performance (specific impulse performance, reusable performance, operation and maintenance, and long-term storage in space, etc.), and has broad application prospects in the fields of launch vehicles, space vehicles, and star surface base construction. For liquid oxygen and methane attitude control engines, the propellant flow rate is small and is prone to phase change due to heat, which will seriously affect the reliability of the engine. Therefore, how to ensure the inlet ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/56F02K9/58F02K9/95
CPCF02K9/56F02K9/58F02K9/95
Inventor 程诚周海清李野戴佳林庆国张志远
Owner SHANGHAI INST OF SPACE PROPULSION
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