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A cryogenic propellant supply system, method and device

A low-temperature propellant and supply system technology, applied in jet propulsion devices, rocket engine devices, jet engine testing, etc., can solve the problems of high difficulty in implementation and complicated test methods, and achieve the effect of stable adjustment

Active Publication Date: 2020-11-06
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, since the temperature of liquid oxygen is below minus 183 degrees Celsius, and the temperature of liquid methane is below minus 161 degrees Celsius, both belong to low-temperature propellants. At present, the most effective solution is to place the engine in a vacuum chamber, but this test method is complicated and difficult to implement

Method used

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  • A cryogenic propellant supply system, method and device
  • A cryogenic propellant supply system, method and device
  • A cryogenic propellant supply system, method and device

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0061] see figure 1 As shown, Embodiment 1 of the present application provides a cryogenic propellant supply system, including: a nitrogen blowing system 101 , an oxidant supply system 102 , a fuel supply system 103 and a low-pressure liquid oxygen cooling system 104 .

[0062] The nitrogen purge system 101 is used for purging the system piping before and after the experiment and testing the air tightness of the cryogenic propellant supply system.

[0063] When the airtightness of the low-temperature propellant supply system is qualified, the oxidizer supply system 102 is used to deliver liquid oxygen to the thrust chamber of the engine; and the fuel supply system 103 is used to supply the thrust chamber of the engine The chamber delivers liquid methane.

[0064] The low-pressure liquid oxygen cooling system 104 is used to cool the pipeline between the solenoid valve (A15, B15) and the thrust chamber of the engine, wherein one solenoid valve (A15) is arranged between the oxid...

Embodiment 2

[0082] see figure 2 As shown, Embodiment 2 of the present application also provides a low-temperature propellant cooling method, including:

[0083] S201: When the oxidant supply system detects that the airtightness of the low-temperature propellant supply system described in Embodiment 1 meets the preset standard, fill the high-pressure liquid oxygen storage tank with liquid oxygen to meet the preset value of liquid oxygen;

[0084] S202: When the liquid oxygen in the high-pressure liquid oxygen storage tank meets the liquid oxygen preset value, cool the pipeline between the liquid oxygen inlet port and the engine thrust chamber, wherein the liquid oxygen inlet port is The liquid oxygen outlet end of the high-pressure liquid oxygen storage tank;

[0085] as well as,

[0086] Cooling the solenoid valve (A15) valve body, and the pipeline between the solenoid valve (A15) valve body and the engine thrust chamber;

[0087] S203: When cooling to the first preset value, after in...

Embodiment 3

[0089] see image 3 As shown, Embodiment 3 of the present application also provides another low-temperature propellant cooling method, including:

[0090] S301: When the fuel supply system detects that the airtightness of the low-temperature propellant supply system described in Embodiment 1 meets the preset standard, fill the high-pressure liquid methane storage tank with liquid methane to meet the preset value of methane;

[0091] S302: When the liquid methane in the high-pressure liquid methane storage tank meets the methane preset value, the pipeline between the coolant methane liquid inlet end and the engine thrust chamber, wherein the liquid methane liquid methane liquid inlet end is a high-pressure liquid The liquid oxygen outlet end of the methane storage tank;

[0092] as well as,

[0093] Cooling the solenoid valve (B15) valve body, and the pipeline between the solenoid valve (B15) valve body and the engine thrust chamber;

[0094] S303: When cooling to the second...

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Abstract

The invention provides a low-temperature propellant supplying system, a method and a device. The low-temperature propellant supplying system comprises a nitrogen blowing away system, an oxidant supplying system, a fuel supplying system and a low-pressure liquid oxygen cooling system; the nitrogen blowing away system is used for carrying out purging operation on a system pipeline before and after an experiment and detecting the air tightness of the low-temperature propellant supplying system; under the condition that the air tightness of the low-temperature propellant supplying system is qualified, the oxidant supplying system is used for conveying liquid oxygen to an engine thrust chamber; the fuel supplying system is used for conveying liquid methane to the engine thrust chamber; the low-pressure liquid oxygen cooling system is used for cooling a pipeline, wherein partial pipeline is located between an electromagnetic valve (A15) and the engine thrust chamber and partial pipeline is located between an electromagnetic valve (B15) and the engine thrust chamber. According to the embodiment of the supplying system, the method and the device, the required preset temperature can be achieved before the test, the low-pressure liquid oxygen cooling system adopts low-pressure liquid oxygen to cool the environment so as to ensure the safety, the propellant conveying amount can be stablyadjusted, and simplicity and reliability are achieved.

Description

technical field [0001] The present application relates to the technical field of rocket engine testing, in particular to a low-temperature propellant supply system, method and device. Background technique [0002] Compared with solid rocket motor technology and solid-liquid hybrid rocket motor technology, liquid rocket engine technology is more mature and has a wider range of applications. Liquid rocket engine has repeatable start, thrust adjustable, high specific impulse, combustion High efficiency and many other advantages occupy an extremely important position in the aerospace industry. [0003] In the past, due to many reasons such as technical level and economic level, a large number of toxic and environmentally harmful liquid propellants, such as methyl hydrazine and dinitrogen tetroxide, were used in liquid rocket engines. In recent years, the increasingly serious environmental problems have led us to explore and find alternative non-toxic high-energy propellants. Th...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/44F02K9/54G01M15/14
CPCF02K9/44F02K9/54G01M15/14
Inventor 俞南嘉赵增张洋韩树焘李闻达
Owner BEIHANG UNIV
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