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Satellite support and carrier rocket

A technology for launch vehicles and satellites, applied in the aerospace field, can solve the problem of many assembly processes, achieve the effect of firm connection, reduce the difficulty of forming process, and improve the overall carrying capacity

Pending Publication Date: 2021-04-30
BEIJING XINGJI RONGYAO SPACE TECH CO LTD +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Therefore, the technical problem to be solved by the present invention is to overcome the defect that there are many assembly processes in the satellite bracket in the prior art, thereby providing a satellite bracket and a launch vehicle with simpler assembly.

Method used

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  • Satellite support and carrier rocket
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  • Satellite support and carrier rocket

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Embodiment Construction

[0060] The technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Apparently, the described embodiments are some of the embodiments of the present invention, but not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0061] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" etc. The indicated orientation or positional relationship is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, ...

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Abstract

The invention relates to the technical field of aerospace, and in particular relates to a satellite support and a carrier rocket. The satellite support comprises a first force bearing structure on which a satellite is arranged, a second force bearing structure which is arranged on the outer side of the first force bearing structure and is suitable for being connected with a control cabin of the carrier rocket, and a connecting structure which is arranged between the first force bearing structure and the second force bearing structure, and the two ends of the connecting structure are connected with the first force bearing structure and the second force bearing structure respectively; the first force bearing structure, the second force bearing structure and the connecting structure are integrally formed. The first force bearing structure, the second force bearing structure and the connecting structure of the satellite support are integrally formed, so that the satellite support only comprises a necessary main body structure, other connecting structures for connecting the main body structure do not need to be additionally arranged, the number of parts is reduced as much as possible, the overall size of the satellite support is reduced, and overall assembling procedures are reduced; the assembly is simple, the weight of the satellite support is reduced, and the overall carrying capacity of the carrier rocket is improved.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a satellite bracket and a launch vehicle. Background technique [0002] In the prior art, the launch vehicle is used as a means of transportation to send the satellite into space, but the satellite is not directly installed on the launch vehicle, and the satellite and the launch vehicle are connected through a satellite bracket, that is, arranged on the last stage control cabin of the launch vehicle A satellite bracket with the same outer diameter as the cabin section. The satellite bracket provides the installation interface for the satellite, bears the load of the satellite during the launch process, and also provides the installation location for key equipment such as cables and laser strapdown inertial measurement combination. [0003] At present, the main load-bearing beam of the satellite support set on the traditional control cabin is generally a "well"-shaped or "octo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/64
CPCB64G1/641
Inventor 彭小波郑立伟李建伟
Owner BEIJING XINGJI RONGYAO SPACE TECH CO LTD
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