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Cabin plate type satellite configuration and assembly method thereof

A technology of satellite configuration and satellite main structure, which is applied to the assembly of satellite systems and satellite configurations, and the field of deck-type satellite configurations. It can solve problems such as high prices, poor reliability, and technical complexity, and achieve high space utilization and reduce The effect of R&D cycle and strong scalability

Inactive Publication Date: 2019-01-18
CHANGGUANG SATELLITE TECH CO LTD
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  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The purpose of the present invention is to propose a deck-type satellite configuration and its assembly method to solve the problems of high price, complex technology and poor reliability in the prior art

Method used

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  • Cabin plate type satellite configuration and assembly method thereof
  • Cabin plate type satellite configuration and assembly method thereof
  • Cabin plate type satellite configuration and assembly method thereof

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Embodiment Construction

[0032] Embodiments of the present invention will be further described below in conjunction with the accompanying drawings.

[0033] See attached figure 1 - attached Figure 4 , a kind of deck type satellite configuration of the present invention comprises:

[0034] Satellite main structure 1, described satellite main structure 1 is the box body structure that is made up of docking plate 102, rear side plate 103, left side plate 104, right side plate 105, upper side plate 106 and lower side plate 108 and is installed in box The satellite load 101 in the body structure, the inside of the box structure is provided with a partition 107; The lower side panels 108 are all honeycomb core sandwich panels with a honeycomb structure; they have the characteristics of light weight and high rigidity; according to task requirements, ensure that the satellite load 101 is reasonably arranged on the honeycomb core sandwich panels to ensure thermal control, wiring and assembly It can be impl...

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Abstract

The invention relates to a cabin plate type satellite configuration and an assembly method thereof, which belongs to the technical field of spacecraft design and aims at solving the problems of high price, complex technology and poor reliability existing in the prior art. A cabin plate type satellite configuration of the present invention includes a main structure of the satellite, a main structure of the main structure of the main structure of the main structure and a main structure of the main structure of the main structure. A considerate windsurfing fixed to one of the lateral walls of themain satellite structure; Two deployment sails arranged on two opposite side walls of the satellite main structure, the two deployment sails being symmetrically arranged about the considerate sails,the deployment sails being inclined with respect to the side walls of the corresponding satellite main structure; And a plurality of legs disposed on a side wall opposite the caring windsurfing. The invention has the advantages of simple and reliable structure, high space utilization rate and good mechanical performance, can realize rapid design and rapid assembly according to task requirements, and has strong expansibility and low cost. Easy to launch multiple satellites with one rocket.

Description

technical field [0001] The invention belongs to the technical field of spacecraft design, and in particular relates to a deck-type satellite configuration, a satellite system and an assembly method of the satellite configuration. Background technique [0002] The task of satellite configuration and layout design is to meet the installation and pointing requirements of payload equipment, meet the pointing and installation requirements of satellite subsystem equipment, and at the same time, the whole star must have good stiffness characteristics, and the proportion of the whole star structure should be reduced as much as possible. , to reduce the moment of inertia to improve maneuverability. Satellites also require final assembly operability and sufficient solar array area to meet energy demands. [0003] At present, most micro-satellites adopt a deck-type structure. The satellite is connected to the rocket through a docking ring. The docking ring is installed on the opposite...

Claims

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Application Information

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IPC IPC(8): B64G1/10
CPCB64G1/10
Inventor 石有胜陈亚东李宁谷松张雷
Owner CHANGGUANG SATELLITE TECH CO LTD
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