Micro-satellite based on integrated electronic integrated cabinet

Abstract

The invention provides a micro-satellite based on an integrated electronic integrated cabinet. The micro-satellite based on an integrated electronic integrated cabinet includes a centralcabin, a propulsion device, a solar cell array and a truss, wherein the satellite coordinate origin is the center of a carry docking surface; +X points to the carrying direction; the opposite side of the fixed solar cell array patch direction is the +Z direction, and +Y is the right-handed system with the two directions; the propulsion device is installed at the top of the central cabin; the solar cell array isconnected to the central cabin by the truss; the central cabin is a plug-in integrated electronic cabinet, including functional board cards and a bottom plate; the bottom plate is parallel to the +Zplane, and is installed at the bottom of the central cabin; and each functional board card is parallel to the bottom plate and is plugged into the cabinet.

Description

technical field [0001] The invention relates to the technical field of satellite configuration, in particular to a micro-satellite structure using an integrated electronic cabin as the main body of the satellite. Background technique [0002] As an important direction of current satellite development, micro-satellites are getting more and more attention. Due to the small size of micro-satellites, satellite loads and on-board equipment are required to be small in size and light in weight. The invention in this paper is in line with the direction of technological development. [0003] The main body of a general satellite is the central cabin or the central cabin. The central cabin uses aluminum honeycomb panels as the main structure. Each functional module is a stand-alone unit of various forms. The connectors are connected. [0004] The common integrated integrated electronic cabin is installed on the structure of the satellite as a piece of equipment of the satellite. The s...

AI Technical Summary

Problems solved by technology

[0009] Existing satellite load-bearing structural panels generally use honeycomb panels with a thickness of more than 20mm. For satellites with a side length of only 200-300mm, the space utilization rate is not high, and the shapes of each stand-alone equipment are inconsistent. Without the use of integrated electronics, Spatial topology configuration will be very difficult and will waste a lot of satellite space

[0010] (3) Many external connectors

In addition to increasing the weight and volume of the socket, it may also increase the risk of wrong insertion of the connector, and frequent insertion will also reduce the reliability of the connector.

[0012] (4) It is not conducive to the realization of modularization and serialization

[0013] The inconsistency of the hardware interface makes modularization and serialization difficult, so that each stand-alone machine needs to be developed independently, increasing the development cycle and development cost

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