Multi-functional bulkhead structure for microsatellite system

A micro-satellite, multi-functional technology, applied in the direction of artificial satellites, etc., can solve the problems of low integration of satellite platform loading space, self-heaviness of power supply subsystem and structural subsystem, etc.

Inactive Publication Date: 2016-08-31
NAT UNIV OF DEFENSE TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The purpose of the present invention is to provide a multi-functional bulkhead structure for micro-satellite system, which solves the problem that the existing discrete power supply subsystem and structure subsystem have a large dead weight, and the integration degree of the satellite platform loading space is not high technical issues

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  • Multi-functional bulkhead structure for microsatellite system
  • Multi-functional bulkhead structure for microsatellite system
  • Multi-functional bulkhead structure for microsatellite system

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[0024] The accompanying drawings constituting a part of this application are used to provide further understanding of the present invention, and the schematic embodiments and descriptions of the present invention are used to explain the present invention, and do not constitute an improper limitation of the present invention.

[0025] see figure 1 , the present invention provides a multifunctional bulkhead structure 100 for a microsatellite system, including a carbon fiber support structure, a lithium-ion battery pack 140, a balanced charging circuit, and an electrical connector for electrical connection with an external power source or electrical equipment 170. The voltage display module 150, the carbon fiber support structure includes a keel 130, a first cover 110 and a second cover 120 respectively placed on one side of the keel 130, a lithium-ion battery pack 140, a balance charging circuit, and an electrical connector 170 and the voltage display module 150 are accommodated...

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Abstract

The present invention provides a multi-functional bulkhead structure for a microsatellite system and relates to the field of designing of spacecraft structures and power supply systems. The multi-functional bulkhead structure comprises a carbon fiber support structure, lithium ion batteries, a balance charging circuit, an electrical connector, a voltage display module and the like, and functions of force bearing, power supplying, balance charging and the like are integrated. According to the multi-functional bulkhead structure, the integrated design of the power subsystem, the structure subsystem and the state detection subsystem is realized, and the issues of long life, heat dissipation and the like of the multi-functional bulkhead structure are fully taken into consideration. The multi-functional bulkhead structure for the microsatellite system has the advantages of small size, light weight, long life, good compatibility with the satellite overall and the like, and the application to a microgravity air flotation simulation satellite shows that the multi-functional bulkhead structure for the microsatellite system effectively reduces the weight of an air flotation simulation satellite body and increases the effective load carrying space of the air flotation simulation satellite.

Description

technical field [0001] The invention relates to the technical field of spacecraft structure and power supply system design, in particular to a multifunctional bulkhead structure for a microsatellite system. Background technique [0002] Microsatellites refer to satellites with a weight of less than 1000kg, which have the characteristics of low cost, short development cycle, and strong functionality after networking. Especially in recent years, with the rapid and practical use of microsatellites (weighting 10kg to 100kg), a large number of microsatellite systems with clear uses have emerged. Such as the "Tiantuo" series satellites of the National Defense University, the "Innovation No. 1" of the Chinese Academy of Sciences, and the "Aerospace Tsinghua No. 1" of Tsinghua University. In order to realize the miniaturization and miniaturization of the satellite, various instruments and equipment contained in it must be miniaturized and integrated as much as possible. For example...

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Application Information

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IPC IPC(8): B64G1/10
CPCB64G1/10
Inventor 范才智李东旭李思侃刘望郝瑞
Owner NAT UNIV OF DEFENSE TECH
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