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Spacecraft propellant metallic diaphragm storage tank fatigue life reliability calculating method

A technology of metal diaphragm and fatigue life, which is applied in the direction of instruments, scientific instruments, strength characteristics, etc., can solve the problems of fatigue life and reliability of tank diaphragms, shorten the test cycle, reduce test costs, and improve reliability high effect

Active Publication Date: 2018-11-30
BEIJING SPACE TECH RES & TEST CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The remaining amount of propellant in the propellant tank of a spacecraft is mainly related to the propellant consumption of the flight mission before the shutdown. Fatigue life and reliability of tank diaphragms under all flight conditions may be verified by limited number of ground tests

Method used

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  • Spacecraft propellant metallic diaphragm storage tank fatigue life reliability calculating method
  • Spacecraft propellant metallic diaphragm storage tank fatigue life reliability calculating method
  • Spacecraft propellant metallic diaphragm storage tank fatigue life reliability calculating method

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Embodiment Construction

[0034]In order to more clearly describe the embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings that are used in the embodiments. Apparently, the drawings in the following description are only some embodiments of the present invention, and those skilled in the art can also obtain other drawings according to these drawings without creative efforts.

[0035] When describing the embodiments of the present invention, the terms "vertical", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", " The orientation or positional relationship expressed by "horizontal", "top", "bottom", "inner" and "outer" is based on the orientation or positional relationship shown in the relevant drawings, which are only for the convenience of describing the present invention and simplifying the description, and It is not to indicate or imply that the device or element referred to must have a particul...

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Abstract

The invention relates to a spacecraft propellant metallic diaphragm storage tank fatigue life reliability calculating method. The spacecraft propellant metallic diaphragm storage tank fatigue life reliability calculating method comprises following steps: a, a relation model of movement of metallic diaphragm in a storage tank with output amount of a propellant from the storage tank is established;b, the metallic diaphragm fatigue life reliability of a specific volume fluctuation amount of the propellant in the storage tank is calculated; c, the metallic diaphragm fatigue life reliability of any volume fluctuation amount of the propellant in the storage tank is calculated. The spacecraft propellant metallic diaphragm storage tank fatigue life reliability calculating method is capable of reducing test frequency obviously, shortening test period, reducing test cost, and is high in calculation result dependability.

Description

technical field [0001] The invention relates to a method for calculating the reliability of the fatigue life of a spacecraft propellant metal diaphragm storage tank. Background technique [0002] The metal diaphragm tank is a commonly used spacecraft propellant tank, which can effectively eliminate the propellant sloshing caused by external disturbance. The metal diaphragm in the storage tank separates the storage tank into two parts, the air chamber and the liquid chamber. The diaphragm is squeezed by the pressurized gas in the air chamber, so that the diaphragm undergoes elastic-plastic deformation and moves in the direction of the liquid chamber. The agent is delivered to the downstream outlet of the storage tank. [0003] When the spacecraft is flying in orbit, it will face the situation that the propulsion system does not need to output propellant for a certain period of time. For example, communication satellites use CMG and momentum wheels for attitude control, and t...

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Application Information

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IPC IPC(8): G01N3/00
CPCG01N3/00G01N2203/0073
Inventor 邵立民
Owner BEIJING SPACE TECH RES & TEST CENT
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