Looking for breakthrough ideas for innovation challenges? Try Patsnap Eureka!

Thermal load analysis method for multi-compartment spacecraft

An analysis method and technology for spacecraft, which are applied to aerospace vehicles, devices for controlling the living conditions of aerospace vehicles, aircraft, etc. Optimized radiator area, increased operating temperature, and reduced weight

Active Publication Date: 2019-02-26
BEIJING SPACE TECH RES & TEST CENT
View PDF3 Cites 0 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

When designed according to the traditional method, due to the artificial increase of the maximum heat load, the surface temperature of the radiator is too low when the heat load is low
At the same time, the operating temperature of the working fluid inside the radiator is too low, resulting in increased viscosity of the working fluid, increased operating resistance, increased power consumption of the circulating pump, and even freezing of the working fluid, resulting in the risk of radiator failure

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Thermal load analysis method for multi-compartment spacecraft
  • Thermal load analysis method for multi-compartment spacecraft

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0033] The description of the embodiments in this specification should be combined with the corresponding drawings, and the drawings should be regarded as a part of the complete specification. In the drawings, the shapes or thicknesses of the embodiments may be exaggerated and marked for simplification or convenience. Furthermore, parts of each structure in the drawings will be described separately. It should be noted that elements not shown in the drawings or described in words are forms known to those of ordinary skill in the art.

[0034] The descriptions of the embodiments here, any references to directions and orientations are just for convenience of description, and should not be construed as any limitation to the protection scope of the present invention. The following descriptions of the preferred embodiments involve combinations of features, which may exist independently or in combination, and the present invention is not particularly limited to the preferred embodime...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

The invention relates to a multi-cabin-section spacecraft heat load analysis method. The multi-cabin-section spacecraft heat load analysis method comprises the steps that (a), the outer heat flow condition of a multi-cabin-section spacecraft under various work modes is analyzed; (b), according to the heat output and uncontrollable heat dissipating quantities in all cabin sections under all modes,the controllable heat dissipating quantities generated in all the cabin sections under all the modes is counted up; and (c), the heat dissipating capacity of all the cabin sections is determined, thecontrollable heat dissipating quantities of the all cabin sections are distributed according to the heat dissipating capacity, and heat dissipating components of all the cabin sections are designed. According to the multi-cabin-section spacecraft heat load analysis method, the weight of a heat management system can be effectively controlled, and the risk of invalid freezing of a radiator is avoided.

Description

technical field [0001] The invention relates to the technical field of overall design of spacecraft, in particular to a thermal load analysis method of a multi-cabin spacecraft. Background technique [0002] At present, the development trend of space stations is large-scale multi-chamber, scalability, and multi-mission missions. For example, the foreign Mir space station and the International Space Station are composed of multiple cabin sections. task, designed a variety of working modes. [0003] The thermal management system of the space station is to control the temperature of the air and equipment in the cabin, and generally uses radiators as heat dissipation components. During the orbital operation of the space station, the internal heat sources mainly include equipment heat production and energy system waste heat Q s , occupant metabolic heat production Q r , the external heat source is mainly the external heat flow Q from the sun and the earth w . After the space...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/50
CPCB64G1/50B64G1/503
Inventor 王宇宁杨宏靳健姚峰张兰涛曲溪孙伊白梵露孙乐丰杨彪汤溢
Owner BEIJING SPACE TECH RES & TEST CENT
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Patsnap Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com