Transient Dynamic Analysis of Gossamer-Appendage Deployment Using Nonlinear Finite Element Method

著录项

• 来源
  《Journal of Spacecraft and Rockets》 |2011年第5期|p.881-890|共10页
• 作者

  Hiraku Sakamoto; Yasuyuki Miyazaki; Osamu Mori;

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• 作者单位

  Tokyo Institute of Technology, Tokyo 152-8552, Japan Structural Dynamics Design Laboratory, Department of Mechanical and Aerospace Engineering, 2-12-1 No. 13-17 Ookayama Meguro-ku;

  Nihon University, Chiba 274-8501, Japan Department of Aerospace Engineering, College of Science and Technology, 7-24-1 Narashinodai, Funabashi;

  Japan Aerospace Exploration Agency, Kanagawa 252-5210, Japan Lunar and Planetary Exploration Group, 3-1-1 Yoshinodai, Chuo-ku Sagamihara;

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• 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
• 原文格式 PDF
• 正文语种 eng
• 中图分类
• 关键词

  A: beam cross-sectional area; A~r: 3×3 matrix defined in Eq. (13); d_(CM): vector pointing from the geometrical center to the center of mass of a satellite bus; E: Young's modulus of beam; E_I~r,e_I~r: nodal base vector in undeformed and deformed configurations at node r (I = 1,2, 3); et al;

  机译：A：梁的截面积;A〜r：等式3中定义的3×3矩阵。 （13）;d_（CM）：从几何中心指向卫星总线质心的矢量;E：梁的杨氏模量;E_Ir;e_Ir：节点r处未变形和变形的节点基向量（I = 1,2;3）;等;