Design and analysis of the composite lattice frame of a spacecraft solar array

被引：18

作者：

Morozov, E. V. ^{[1
]}

Lopatin, A. V. ^{[2
]}

机构：

[1] Australian Def Force Acad, Univ New S Wales, Sch Informat Technol & Engn, Canberra, ACT, Australia

[2] Siberian State Aerosp Univ, Dept Aerosp Engn, Krasnoyarsk, Russia

来源：

COMPOSITE STRUCTURES | 2011年 / 93卷 / 07期

关键词：

Spacecraft solar array; Composite lattice frame; Vibration analysis; Finite-element modelling; Design optimisation;

D O I：

10.1016/j.compstruct.2010.12.007

中图分类号：

O3 [力学];

学科分类号：

08 ; 0801 ;

摘要：

A novel design of the composite structural lattice frame for the spacecraft solar arrays is presented in the paper. The frame is composed of two flat lattice composite plates assembled into the three-dimensional panel using frame-like connectors. Design, fabrication, modelling and modal analysis of the panel solar arrays based on the proposed technology are discussed. The lattice panels are modelled as three-dimensional frame structures composed of beam elements subjected to the tension/compression, bending and torsion using the specialised finite-element model generator/design modeller. Results of the calculations of the frequencies and vibration forms for the lattice panels with various types of supports imitating the ways the panels can be attached to the spacecraft body, deployment must, and adjacent solar panels are presented and discussed. The lattice frame design for maximum fundamental frequency is performed subject to constraints imposed on the geometrical parameters of the solar panel. (C) 2011 Elsevier Ltd. All rights reserved.

引用

页码：1640 / 1648

页数：9

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