Paper Title:
Development of a Novel Deployment Hinge Mechanism for a Spacecraft Using Axiomatic Design
  Abstract

This paper presents a novel hinge mechanism for deployment of spacecraft subsystems such as antennas, solar arrays. By using Axiomatic design theory, the conceptual design of the hinge mechanism is suggested, which has not only high deployed stiffness and low deployment shock but also does not require lubrication and accurate fabrication. That is, optimization of deployment torque and maximization of the deployed stiffness can be possible since this suggested hinge mechanism is decoupled design. And the suggested hinge mechanism is fabricated and tested to evaluate the feasibility. Quasi-static analysis is performed to optimize deployment torque for low deployment shock by using FEM. Also, the bending stiffness is measured by 4 point bending test.

  Info
Periodical
Advanced Materials Research (Volumes 314-316)
Chapter
Mechanical Behavior & Fracture
Edited by
Jian Gao
Pages
863-871
DOI
10.4028/www.scientific.net/AMR.314-316.863
Citation
J. W. Jeong, Y. I. Yoo, J. J. Lee, J. H. Lim, K. W. Kim, D. S. Hwang, "Development of a Novel Deployment Hinge Mechanism for a Spacecraft Using Axiomatic Design", Advanced Materials Research, Vols. 314-316, pp. 863-871, 2011
Online since
August 2011
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Price
$32.00
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