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A fast modeling method and system for spacecraft solar wing dynamics

A technology of wing dynamics and modeling method, applied in the field of aerospace vehicles, it can solve the problems of uncollected data, no explanation or report found, lengthy analysis process, etc., to achieve effective dynamic analysis and iterative optimization, and shorten the development cycle. Effect

Active Publication Date: 2017-02-15
SHANGHAI ASES SPACEFLIGHT TECH LTD CO
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AI Technical Summary

Problems solved by technology

In the past, the dynamic modeling of solar wings was done manually, the analysis process was lengthy, and iterative optimization was difficult, making it difficult to speed up the design cycle of solar wings
[0003] At present, there is no description or report of the similar technology of the present invention, and no similar data at home and abroad have been collected yet.

Method used

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  • A fast modeling method and system for spacecraft solar wing dynamics
  • A fast modeling method and system for spacecraft solar wing dynamics
  • A fast modeling method and system for spacecraft solar wing dynamics

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Embodiment

[0044] like Figure 3-8 As shown, the present embodiment provides a method for rapid modeling and design optimization of spacecraft solar wing dynamics, the method includes the following steps:

[0045] Step 1: Determine the design parameters of the solar wing; the present invention selects a total of 17 structural parameters, specifically: 1) the number of substrates N1; 2) the length of the substrate L1; 3) the width of the substrate H1; 4) the length of the short side of the connecting frame H3 ;5) The length of the long side of the connecting frame H2; 6) The length of the connecting frame L2; 7) The distance between the plates in the unfolded state D2; 8) The length of the root hinge D1; 9) The cross-sectional width of the connecting frame L3; 10) The cross-sectional height of the connecting frame H4; 11) Connecting frame section thickness T3; 12) substrate panel thickness T1; 13) substrate honeycomb thickness T2; 14) number of pressing points N2; 15) pressing point long ...

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Abstract

The invention discloses a spacecraft solar wing dynamics rapid modeling method and system. Design parameters of a spacecraft solar wing are determined, a finite element analytical model of the solar wing is generated automatically through a program, analysis software is called for conducting dynamics analysis on the solar wing model, the whole spacecraft solar wing dynamics simulation analysis process is completed automatically, and the spacecraft solar wing dynamics rapid modeling method and system are economical and efficient. The spacecraft solar wing dynamics rapid modeling method and system can be widely applied to spacecraft solar wing dynamics automatic simulation analysis design, can rapidly and effectively conduct dynamics analysis and iterative optimization on the solar wing, and greatly shorten the research and development cycle of the solar wing.

Description

technical field [0001] The invention relates to the technical field of aerospace vehicles, in particular to a fast modeling method and system for the dynamics of a solar wing of a spacecraft. Background technique [0002] At present, most of the deployable solar wings mainly adopt the structural form of the interconnection of the composite material substrate and the hinge between the panels. After orbiting, it automatically unlocks and unfolds to provide power for the spacecraft to work in orbit, which is an indispensable part of every spacecraft. As a large flexible part of the spacecraft, the dynamic performance of the solar wing in the retracted state and the deployed state is very important, which directly affects the frequency shift design of the active segment of the secondary structure of the spacecraft, and the attitude control and load of the entire star after deployment in orbit. Therefore, It is necessary to carry out kinetic analysis on it. In the past, the dyn...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
Inventor 刘汉武张华胡震宇李东颖
Owner SHANGHAI ASES SPACEFLIGHT TECH LTD CO
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