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Liquid rocket engine starter and design method thereof

A technology of liquid rocket and design method, which is applied to rocket engine devices, machines/engines, mechanical equipment, etc., can solve problems such as large volume and complex structure, and achieve the effects of simple process, reduced leakage links, and high reliability

Active Publication Date: 2021-01-08
北京天兵科技有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

lead to complex structure and bulky

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  • Liquid rocket engine starter and design method thereof

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[0028] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in combination with specific embodiments and with reference to the accompanying drawings. It should be understood that these descriptions are exemplary only, and are not intended to limit the scope of the present invention. Also, in the following description, descriptions of well-known structures and techniques are omitted to avoid unnecessarily obscuring the concept of the present invention.

[0029] Such as figure 1 As shown, the present invention provides a kind of liquid rocket engine starter, comprises propellant storage tank 1, adds discharge valve 4, solenoid valve 5, gas generator 7 and igniter 6; Stores nontoxic and For the self-pressurized nitrous oxide-based composite propellant, both gaseous and liquid propellants are stored in the propellant storage tank 1. Since the saturated vapor pressure of the...

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Abstract

The invention relates to a liquid rocket engine starter and a design method thereof. The liquid rocket engine starter is provided with a propellant storage tank, a filling and discharging valve, an electromagnetic valve, a fuel gas generator and an igniter, a non-toxic self-pressurization propellant is stored in the propellant storage tank, and due to the fact that the saturated vapor pressure ofa medium is high, driving pressure can be provided for the propellant through the pressure of the medium; and the filling and discharging valve is connected to a connecting pipeline of the storage tank and the electromagnetic valve to fill and discharge the non-toxic self-pressurization medium, the rear portion of the electromagnetic valve is connected with an inlet of the fuel gas generator through a pipeline, the propellant is ignited to generate fuel gas, the fuel gas enters a downstream turbine shell at a high speed and pushes a turbine to rotate, and starting of an engine is achieved. Theliquid rocket engine starter adopts the nitrous oxide-based composite propellant, and has the advantages of being green, non-toxic, high in saturated vapor pressure, high in specific impulse, low inuse cost and easy to maintain; and the starter is simple in structure, light in weight, non-toxic and pollution-free, can be started for multiple times, and can be repeatedly used.

Description

technical field [0001] The invention relates to the technical field of liquid rockets, in particular to a liquid rocket engine starter and a design method thereof. Background technique [0002] With the rapid development of the aerospace industry, various technologies related to rockets have also achieved rapid progress. The liquid rocket engine is an important subsystem of the rocket, and the starter is an important component of the liquid rocket engine, which provides initial power for the engine to start. [0003] Among the liquid rocket engine starters commonly used at present, the solid starter cannot achieve multiple starts, and the gas starter has a large structural mass when used for multiple starts. The liquid starter needs to provide a complete set of extrusion system, which has a complex structure. Moreover, solid starters and liquid starters usually use toxic media, which do not meet the requirements of future rockets that are green, environmentally friendly, no...

Claims

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Application Information

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IPC IPC(8): F02K9/95
CPCF02K9/95
Inventor 沈涌斌田伟枫康永来朱正辉
Owner 北京天兵科技有限公司
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