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Differential temperature control system and method for spaceborne stand-alone

A temperature control system and differentiated technology, applied in the field of aerospace applications, can solve problems such as low efficiency of on-orbit temperature control, and achieve the effect of eliminating influence, reducing thermal control resource requirements, and improving control accuracy

Active Publication Date: 2021-06-08
INNOVATION ACAD FOR MICROSATELLITES OF CAS +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The purpose of the present invention is to provide a space-borne stand-alone differential temperature control system and method to solve the problem of low efficiency of on-orbit temperature control of the existing space-borne stand-alone spacecraft

Method used

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  • Differential temperature control system and method for spaceborne stand-alone
  • Differential temperature control system and method for spaceborne stand-alone

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Embodiment Construction

[0035] The satellite-borne stand-alone differential temperature control system and method proposed by the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. Advantages and features of the present invention will be apparent from the following description and claims. It should be noted that all the drawings are in a very simplified form and use imprecise scales, and are only used to facilitate and clearly assist the purpose of illustrating the embodiments of the present invention.

[0036] In addition, unless otherwise stated, features in different embodiments of the present invention can be combined with each other. For example, a feature in the second embodiment may be used to replace a corresponding or functionally identical or similar feature in the first embodiment, and the resulting embodiment also falls within the scope of disclosure or description of the present application.

[0037] The co...

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Abstract

The present invention provides a space-borne stand-alone differentiated temperature control system and method, comprising: a first stand-alone module configured to conduct heat with the mounting plate of a spacecraft; a second stand-alone module configured to communicate with radiation through a closed-loop conduction module The maximum normal operating temperature of the components of the second stand-alone module is lower than the maximum normal operating temperature of the components of the first stand-alone module; the minimum normal operating temperature of the components of the second stand-alone module is greater than The minimum normal operating temperature of components of the first stand-alone module.

Description

technical field [0001] The invention relates to the technical field of aerospace applications, in particular to a space-borne stand-alone differential temperature control system and method. Background technique [0002] The purpose of satellite thermal control technology is to control the heat exchange process inside and outside the satellite, so that the thermal balance temperature of the equipment on the satellite is within the required range. Thermal control technology is an important part of aerospace technology, and its design level and quality affect the working status, life and reliability of the entire satellite. With the continuous development of aerospace technology, the application range of satellites is gradually expanding, and the payloads on the satellites vary greatly due to different functions. Therefore, satellite thermal control technology is constantly facing new challenges. [0003] In the thermal control design process of spacecraft space-borne stand-al...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D23/32
CPCG05D23/32
Inventor 马二瑞孙小雷蒋桂忠林士峰任烜许红阳张筱娴张磊
Owner INNOVATION ACAD FOR MICROSATELLITES OF CAS
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