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Ground integration test device and method for cryogenic propellant thermodynamic exhaust system

A low-temperature propellant and exhaust system technology, which is used in simulation devices for space navigation conditions, transportation and packaging, space navigation equipment, etc. simple structure

Active Publication Date: 2021-03-26
CHINA ACAD OF LAUNCH VEHICLE TECH
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Problems solved by technology

[0006] In order to overcome the deficiencies in the prior art, the inventors have carried out dedicated research and provided a ground-integrated test device and method for a low-temperature propellant thermodynamic exhaust system, which implements effectiveness tests of various exhaust methods on the ground to solve the problem of low-temperature propulsion. The problem of effective venting under the condition that the agent is on orbit for a long time and gas-liquid is difficult to separate, thus completing the present invention

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  • Ground integration test device and method for cryogenic propellant thermodynamic exhaust system
  • Ground integration test device and method for cryogenic propellant thermodynamic exhaust system

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Embodiment Construction

[0030] The following describes the present invention in detail, and the features and advantages of the present invention will become more clear and definite along with these descriptions.

[0031] According to the first aspect of the present invention, a kind of low temperature propellant thermodynamic exhaust system ground integration test device is provided, such as figure 1 As shown, it includes a storage tank 1, a vacuum container 2, an active thermodynamic exhaust system, and a passive thermodynamic exhaust system, wherein the storage tank 1 is located inside the vacuum container 2 and is fixedly connected with the inner wall of the vacuum container 2, and the storage tank 1 is connected with the vacuum container 2. The interlayer between the vacuum containers 2 is evacuated by a vacuum unit 21;

[0032]The active thermodynamic exhaust system includes a throttling fluid circuit and a circulating fluid circuit, wherein the throttling fluid circuit includes a first throttle...

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Abstract

The invention provides a cryogenic propellant thermodynamic exhaust system ground integration test device and method, the cryogenic propellant thermodynamic exhaust system ground integration test device comprises a storage tank (1), a vacuum container (2), an active thermodynamic exhaust system and a passive thermodynamic exhaust system, the storage tank (1) is located in the vacuum container (2)and is fixedly connected with the inner wall of the vacuum container (2); an interlayer between the storage tank (1) and the vacuum container (2) is vacuumized through a vacuum unit (21) to simulate the outer space environment. According to the ground integration test device and method, various exhaust schemes and combinations thereof can be tested, most test structural parts in each scheme are arranged outside the storage tank, maintenance is convenient, and the design reliability is improved; structural parts such as a jet mixing device arranged in the storage tank are simple in structure and high in stability.

Description

technical field [0001] The invention belongs to the technical field of low-temperature propellant space on-orbit storage, and in particular relates to a ground integration test device and method for a low-temperature propellant thermodynamic exhaust system. Background technique [0002] Liquid hydrogen and liquid oxygen cryogenic propellants are considered to be the most efficient chemical propellants for space and orbit transfer, and have been widely used in domestic and foreign launch vehicles and upper stages. However, due to the low boiling point of the low-temperature propellant, it is easy to evaporate when heated, causing the pressure of the low-temperature storage tank to rise and exhaust, resulting in a large amount of evaporation loss of the propellant. Take away a large amount of liquid propellant, causing unnecessary losses. [0003] Domestic low-temperature rockets currently in service all adopt the bottom-sinking direct exhaust scheme, but with the increase of...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G7/00
CPCB64G7/00B64G2007/005
Inventor 张少华周振君潘瑶王思峰刘欣巩萌萌王领华吕建伟余群石铄杨勇
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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