Load platform separated type remote sensing microsatellite configuration and assembly method thereof

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

Active Publication Date: 2019-03-19
AEROSPACE DONGFANGHONG DEV LTD
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  • Abstract
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  • 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

Method used

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  • Load platform separated type remote sensing microsatellite configuration and assembly method thereof
  • Load platform separated type remote sensing microsatellite configuration and assembly method thereof
  • Load platform separated type remote sensing microsatellite configuration and assembly method thereof

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

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

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Abstract

The invention provides a low-orbit load platform separated remote sensing microsatellite configuration including a platform metal frame plate structure, a load bracket integrated structure, a frame separation mechanism, a plate type solar wing deployment mechanism and various devices. In a frame plate type structure, similar to a conventional base plate, side plate and top plate type structure, all structural plates adopt a thin metal plate + rib + lightening design; the whole structure adopts the base plate as the design and assembly standard, and a main force transferring route is from the base plate, to the side plate, to the top plate and then to the load. The load bracket integrated structure is mounted on a satellite top plate. A bracket can be connected to the top plate, the bracketcan be provided with a partial air-oriented device and can also be connected to a solar wing, the solar wing includes a one-fold fixing and two-folding unfolding type solar wing, and the solar wing is connected to the satellite side plate and the top plate bracket mainly through a fixing type solar wing. The microsatellite configuration has high space utilization, compact structure and small size, the final assembly process is good in openness, the test is convenient, and the configuration is not adjusted under the conditions of replacing the load 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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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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