Active evaporation control method applicable to long-term on-orbit storage of cryogenic propellant

A low-temperature propellant and active control technology, applied in jet propulsion devices, machines/engines, rocket engine devices, etc., can solve problems such as increased pressure in spacecraft storage tanks and loss of low-temperature propellants, and achieve reduced evaporation losses and good cost , the effect of lowering the temperature

Active Publication Date: 2017-05-31
CHINA ACAD OF LAUNCH VEHICLE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

[0003] The evaporation of low-temperature propellant will increase the pressure of the spacecraft storage tank rapidly. In order to ensure the normal working

Method used

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  • Active evaporation control method applicable to long-term on-orbit storage of cryogenic propellant
  • Active evaporation control method applicable to long-term on-orbit storage of cryogenic propellant
  • Active evaporation control method applicable to long-term on-orbit storage of cryogenic propellant

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Embodiment Construction

[0036] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0037] The active control method of the evaporation amount applicable to the long-term on-orbit storage of low-temperature propellant is realized by the active control device of the evaporation amount. Such as figure 1 Shown is a schematic structural diagram of the active control device for evaporation of the present invention. It can be seen from the figure that the active control device for evaporation of the present invention includes a composite insulation layer 1, a steam cooling screen 2, a heat exchanger 5, a throttling assembly 4, a circulation pump 8, a safety exhaust Air valve 6, steam cooling panel exhaust valve 7 and bypass valve 10, wherein heat exchanger 5 includes inlet pipeline and outlet pipeline.

[0038] (1), first, the active control device for evaporation is installed on the propellant storage tank 3, and the specific insta...

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Abstract

The present invention relates to an active evaporation control method applicable to long-term on-orbit storage of a cryogenic propellant. According to the method, an active evaporation control device that comprises a composite thermal insulating layer, a steam cooling shield, a heat exchanger, a throttling assembly, a circulating pump, a bypass valve and a steam cooling shield exhaust valve is installed for a propellant storage tank. According to the present invention, with the developed active evaporation control method for a cryogenic propellant, discharge of a small amount of simple gaseous propellant can be achieved under the circumstance of uncertain gas-liquid position under microgravity condition, and pressure control on the cryogenic propellant storage tank and control on evaporation of the cryogenic propellant may be effectively realized under dual action by fully using thermodynamic enthalpy of the discharged cryogenic propellant after being throttled; and the method can allow effective reduction of evaporation loss of the cryogenic propellant in on-orbit use, thus prolonging the on-orbit mission time of a spacecraft.

Description

technical field [0001] The invention relates to an active control method suitable for long-term on-orbit storage of low-temperature propellant, which is suitable for the design of a spacecraft low-temperature storage system and realizes long-term on-orbit storage of low-temperature propellant. Background technique [0002] Cryogenic propellants have been widely used in launch vehicles and upper stages at home and abroad because of their high specific impulse, non-toxic, non-polluting, and relatively low price. Cryogenic propellant is considered to be the most economical and efficient chemical propellant for entering space and orbit transfer, and it is also the preferred propellant for future human lunar exploration, Mars exploration and longer-distance deep space exploration. Although low-temperature propellant has high performance, its boiling point is low (liquid hydrogen -253°C, liquid oxygen -183°C), and it is easy to evaporate due to heat, so it is difficult to store fo...

Claims

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Application Information

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IPC IPC(8): F02K9/60
CPCF02K9/60F02K9/605
Inventor 张晓屿张少华贲勋潘瑶余群王思峰吕建伟刘欣王领华王海英巩萌萌王颖昕
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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