FINITE-ELEMENT MODEL FOR THE THERMOELASTIC ANALYSIS OF LARGE COMPOSITE SPACE STRUCTURES Academic Article uri icon

abstract

  • A finite-element model that performs an integrated thermoelastic analysis of large composite space structures is outlined. The model allows for temperature gradients within structural member cross sections and for bending of the members themselves. Nonlinear effects such as radiation boundary conditions and temperature-dependent material properties are also included. Once the model is outlined, a preliminary investigation into the importance of thermally induced forces and moments is carried out. The problem chosen is that of a long cantilevered lattice boom in a geosychronous orbit. For the structure and loading chosen, no significant dynamic responses, such as vibration, occurred. In addition, thermally induced axial forces were the predominant type of loading. For this problem, thermally induced moments could be neglected. The magnitude of axial stresses generated by the transition from shadow to sunlight is on the order of 30% of yield stress. American Institute of Aeronautics and Astronautics, Inc., 1987, All rights reserved.

published proceedings

  • JOURNAL OF SPACECRAFT AND ROCKETS

author list (cited authors)

  • LUTZ, J. D., ALLEN, D. H., & HAISLER, W. E.

citation count

  • 20

complete list of authors

  • LUTZ, JD||ALLEN, DH||HAISLER, WE

publication date

  • January 1987