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Satellite solar cell array rapid design system and method

A solar cell array and design system technology, applied in the aerospace field, to improve work standardization and quality, improve research and development management efficiency, and reduce repetitive labor

Inactive Publication Date: 2019-04-16
SHANGHAI AEROSPACE SYST ENG INST
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  • Abstract
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  • Claims
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Problems solved by technology

[0013] The present invention provides a satellite solar cell array rapid design system and method to solve various deficiencies in the existing satellite solar cell array design technology

Method used

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  • Satellite solar cell array rapid design system and method
  • Satellite solar cell array rapid design system and method

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Embodiment Construction

[0047] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0048] The terms "first", "second", "third", "fourth", etc. (if any) in the description and claims of the present invention and the above drawings are used to distinguish similar objects and not necessarily Describe a particular order or sequence. It is to be understood that the data so used are interchangeable under appropriate circumstances such that the embodiments of the invention described herein can be practiced in sequences other than those illustrated ...

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Abstract

The invention provides a satellite solar cell array rapid design system and method, and the system comprises a skeleton rapid design module which is used for obtaining input solar cell array overall parameters, and generating an overall skeleton model of a solar cell array according to overall main technical indexes; a single-machine rapid design module used for finishing single-machine detailed design work of each part of the solar cell array and generating a single-machine model; and an overall assembly module used for performing overall assembly of the overall framework and the single-machine model according to the overall framework model and the single-machine model to obtain an overall assembly model. According to the method, when the design is executed, an overall framework model ofthe solar cell array is generated firstly, then detailed design models of all single machines are generated, and finally all the single machine models are assembled to form an overall assembly model.According to the system and the method, the design process of the solar cell array is standardized by adopting a top-down design method, full automation of the modeling process is realized, the product development period can be shortened, and the product design quality is improved.

Description

technical field [0001] The invention relates to the aerospace field, in particular to a satellite solar cell array rapid design system and method. Background technique [0002] With the increase of satellite model development tasks, the continuous improvement of user needs, and the faster and faster technological progress, the complexity of satellite solar array products is also getting higher and higher, and the development cycle is getting shorter and shorter. The overall performance of the product, The control of development progress, development process and cost has also become more and more difficult, which have seriously restricted the improvement of independent design and innovative design capabilities, as shown in: [0003] (1) Design "complex operations and many repetitive tasks". [0004] Satellite solar array products need to go through a series of operations from design to simulation analysis, such as: parameter setting, task delivery, design of each stand-alone...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/20
Inventor 王栋梁崔琦峰王威孙世超詹军海白沐炎蒋凌海朱灵严伟杜江华李明钟汉田陈鸿
Owner SHANGHAI AEROSPACE SYST ENG INST
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