Low-temperature propelling system based on steam cooling screen

A technology of steam cooling and low-temperature propulsion, which is applied in the direction of jet propulsion devices, rocket engine devices, machines/engines, etc. It can solve problems such as propellant waste, achieve the effect of prolonging on-orbit working time and solving the effect of short on-orbit working time

Inactive Publication Date: 2018-09-28
BEIJING ONESPACE TECH CO LTD
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

[0006] The main purpose of this application is to provide a low-temperature propulsion system based on a s...

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  • Low-temperature propelling system based on steam cooling screen
  • Low-temperature propelling system based on steam cooling screen
  • Low-temperature propelling system based on steam cooling screen

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Embodiment Construction

[0026] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiment of the application will be clearly and completely described below in conjunction with the accompanying drawings in the embodiment of the application. Obviously, the described embodiment is only It is an embodiment of a part of the application, but not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts shall fall within the scope of protection of this application.

[0027] It should be noted that the terms "first" and "second" in the description and claims of the present application and the above drawings are used to distinguish similar objects, but not necessarily used to describe a specific sequence or sequence. It should be understood that the data so used may be interchanged under appropriate circumstances for...

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Abstract

The invention discloses a low-temperature propelling system based on a steam cooling screen. The low-temperature propelling system comprises a first storage box and a second storage box. A first isolating valve is arranged at an outlet of the first storage box, and a second isolating valve is arranged at an outlet of the second storage box. The first storage box is provided with a propellant managing device, a storage box shell, the steam cooling screen and a multi-layer thermal insulation material. The first storage box sequentially comprises the storage box shell, the steam cooling screen and the multi-layer thermal insulation material from interior to exterior. The propellant managing device is arranged in the first storage box. The storage box shell and the steam cooling screen are connected through a low-temperature thermal insulation support. The problem that the on-orbit working time of a low-temperature propelling system is short is solved. Propellant steam in the steam coolingscreen is utilized as a fuel cell working medium, an internal combustion engine is utilized to drive an electric generator, and electricity utilization demands of working of the propelling system arerelieved. In addition, evaporation and discharging of propellants in the storage boxes are reduced through the low-temperature propelling system, thermal stratification of the propellants in the storage boxes is reduced, and the on-orbit working time of the propelling system is prolonged.

Description

technical field [0001] This application relates to the field of liquid rocket propulsion systems, in particular, to a low-temperature propulsion system based on steam cooling panels, which can be applied to upper stages, satellites, spaceships, interstellar probes and space stations. Background technique [0002] Due to its high specific impulse, non-toxic, non-polluting, and relatively low price, low-temperature propellants have become the preferred propellants for spacecraft entering space and orbit, lunar and deep space exploration. [0003] The inventors found that although the low-temperature propellant has high performance, it is difficult to store due to its low boiling point and easy evaporation. However, the existing propulsion system cannot reduce the evaporation and emission of the propellant in the tank, and at the same time reduce the thermal stratification of the propellant in the tank, and the working time of the entire low-temperature propulsion system on orb...

Claims

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Application Information

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IPC IPC(8): F02K9/44F02K9/60
CPCF02K9/44F02K9/60
Inventor 穆小强
Owner BEIJING ONESPACE TECH CO LTD
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