Configuration and assembly method of remote sensing micro-satellite with separate payload platform

A micro-satellite and assembly method technology, applied in the field of spacecraft, can solve the problems of low space occupancy rate, large satellite envelope, complex ground assembly operation, etc., and achieve low cost, large rigidity margin, and less satellite envelope Effect

Active Publication Date: 2022-04-22
AEROSPACE DONGFANGHONG DEV LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This kind of traditional satellite configuration is a good layout scheme for large satellites (hundred kilograms or tons), but for small satellites, to a certain extent, it has low space occupancy rate, large satellite envelope, and ground Disadvantages such as complicated assembly operations

Method used

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  • Configuration and assembly method of remote sensing micro-satellite with separate payload platform
  • Configuration and assembly method of remote sensing micro-satellite with separate payload platform
  • Configuration and assembly method of remote sensing micro-satellite with separate payload platform

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Embodiment Construction

[0022] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0023] Such as Figure 1-2 As shown, the remote sensing microsatellite configuration of the present invention includes a base plate 1, side plates 2-5, and a top plate 6. The six structural plates are connected to each other through structural protrusions and connection holes on the edge of the plate to form a cuboid closed structure (platform metal frame plate structure), the bracket 7 (load bracket integrated structure) is installed on the upper surface of the top plate 6. The two camera loads 8 given in this embodiment are installed on the same metal base 9, and the metal base is connected to the top plate 6 through fasteners. The solar wing 10 is connected to the threaded hole on the fixed wing through the through hole of the structural side plate 4 and the through hole of the bracket. The structure is connected (plate-type solar wing dep...

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Abstract

The invention provides a remote sensing microsatellite configuration with a low-orbit load platform separated, including a metal frame-plate structure of the platform, an integrated load support structure, a frame-type separation mechanism, a plate-type solar wing deployment mechanism and various equipment. In the frame-plate structure, it is similar to the traditional bottom plate, side plate and roof plate. All structural plates adopt thin metal plate + rib + lightening design; the whole structure is designed and assembled based on the bottom plate. The main force transmission path is from the bottom plate to the side plate to The roof to the load; the integrated structure of the load bracket is installed on the satellite roof; the roof can be connected to the bracket, which can be installed with part of the sky-facing equipment and can also be connected to the solar wing; It is mainly connected to the satellite side panels and roof brackets through fixed solar fins. The satellite configuration space utilization of the invention is high, the structure is compact, the volume is small, the assembly process is open, the test is convenient, and the configuration can not be adjusted under the load replacement situation of the same magnitude.

Description

technical field [0001] The invention relates to the technical field of spacecraft, in particular to a load platform-separated remote sensing micro-satellite configuration and an assembly method thereof. Background technique [0002] In recent years, with the improvement of payload resolution and the increase of spectral bands, high-resolution commercial remote sensing satellites are developing more and more rapidly. In order to meet the high installation, pointing, accuracy requirements and fast maneuvering of payload equipment, currently, the configurations surrounding commercial remote sensing satellites are mainly divided into two types, one is the configuration form of platform load integration, and the other is Platform and load separation configuration. [0003] The platform load integration configuration is mostly used in the occasions where the load is large and the satellite is heavy. In order to ensure the accuracy of the load and good mechanical conditions, the i...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/10
CPCB64G1/10
Inventor 高鸽张帝陈琦李春刘剑
Owner AEROSPACE DONGFANGHONG DEV LTD
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