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A rapid assembly satellite structure

A satellite structure and fast technology, applied in the direction of artificial satellites, etc., can solve the problems of weak load adaptability and long assembly cycle, and achieve the effect of strong load adaptability, simple structure and wide application prospects

Active Publication Date: 2015-07-15
SHANGHAI SATELLITE ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
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Problems solved by technology

[0004] In order to solve the problems of development, long assembly period and weak load adaptability in the prior art, the purpose of the present invention is to provide a fast assembly satellite structure

Method used

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  • A rapid assembly satellite structure
  • A rapid assembly satellite structure

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Embodiment Construction

[0015] Preferred embodiments of the present invention will be described below in conjunction with the accompanying drawings.

[0016] The satellite structure of the present invention is composed of a body structure and a propulsion cabin, which provides an installation basis for instruments and equipment, and should be able to withstand various mechanical environments during satellite launch; it can be independently formed into a cabin during ground testing and assembly.

[0017] attached figure 1 It is a structural schematic diagram of a rapid assembly satellite structure. As shown in the embodiment of the drawings, the device includes: a body structure 1 and a propulsion cabin 2, the body structure 1 includes a carbon fiber frame 101, and the carbon fiber frame 101 includes a regular hexagonal prism frame, a regular hexagonal bottom plate and a beam, so A crossbeam is installed between every two ribs of the frame of the regular hexagonal prism, and the crossbeam is parallel...

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Abstract

The invention discloses a rapid assembly satellite structure, comprising: a body structure [1] and a propulsion cabin [2]; the body structure [1] is composed of a carbon fiber frame (including a bottom plate) [101], a lower partition [102], a middle plate [103], upper bulkhead [104], side plate [105] and top plate [106] are formed; Propelling compartment [2] is made up of load-bearing tube [20]] and propelling compartment bottom plate [202]. The invention solves the problems of long development and assembly period, weak adaptability to loads, etc., and achieves beneficial effects such as simple structure, light weight, rapid assembly, strong expandability, and strong adaptability.

Description

technical field [0001] The invention relates to a satellite structure configuration, in particular to a rapidly assembling satellite structure. Background technique [0002] The satellite structure is a load-bearing structure that provides the installation space and location of the loaded instruments and equipment, bears the static and dynamic loads acting on the satellite, and supports it to complete the predetermined task on the predetermined orbit after entering orbit, and carries the main load of the satellite. It is a satellite system. important component. It has the characteristics of strict quality requirements, limited structural space, ability to adapt to special space environments, high reliability, and integrated design. At present, the development of satellites is facing difficulties such as short development cycle and multiple tasks. Therefore, the structural design must consider the aspects of simple structure, light weight, rapid assembly, strong expandabilit...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/10
Inventor 吕凯顾志悦张宗华范凯
Owner SHANGHAI SATELLITE ENG INST
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