Angular motion equations for a satellite with hinged flexible solar panel

被引：7

作者：

Ovchinnikov, M. Yu. ^{[1
]}

Tkachev, S. S. ^{[1
]}

Roldugin, D. S. ^{[1
]}

Nuralieva, A. B. ^{[1
]}

Mashtakov, Y. V. ^{[1
]}

机构：

[1] Keldysh Inst Appl Math, Moscow, Russia

来源：

ACTA ASTRONAUTICA | 2016年 / 128卷

基金：

俄罗斯科学基金会;

关键词：

Non-linear model; Flexible element; Normal mode; Hinged solar panel; Finite element method; FEM;

D O I：

10.1016/j.actaastro.2016.07.038

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Non-linear mathematical model for the satellite with hinged flexible solar panel is presented. Normal modes of flexible elements are used for motion description. Motion equations are derived using virtual work principle. A comparison of normal modes calculation between finite element method and developed model is presented. (C) 2016 IAA. Published by Elsevier Ltd. All rights reserved.

引用

页码：534 / 539

页数：6

共 9 条

[1]

Gasbarri P., 2014, ACTA ASTRONAUT, V104, P276

[2]

Junkins J.L., 1993, AIAA ED SERIES

[3] EQUATIONS OF MOTION FOR MANEUVERING FLEXIBLE SPACECRAFT [J].