Thermal-structural dynamic analysis of a satellite antenna with the cable-network and hoop-truss supports

Thermally induced structural disturbances of the flexible appendages on a satellite usually occur during eclipse transitions. As a large-scale space structure consists of rod members, cyclic thermal shock induced vibrations such as the divergent thermal flutter may be crucial for its functional serving. In this article, the motivation is to estimate the dynamical behaviors of the AstroMesh antenna under solar flux shock. For this purpose, we developed a numerical approach for the thermal-structural coupling analysis of tensegrity structures considering the pre-stressed state after the form-finding process. The Euler-Bernoulli beam theory, the pre-stressed bar model, and the Fourier thermal element are employed in conjunction with the special consideration on the effect of structural deformations on absorbing solar flux. It is found that, unlike the single boom structure, thermal deformations of the AstroMesh antenna are mainly caused by the temperature variation along rod axis-direction, rather than the temperature gradient on rod cross-section. Besides, the phenomenon of thermally induced vibrations can hardly happen in the AstroMesh antenna.