On-orbit thermal-mechanical coupling performance analysis of a deployed hoop-column antenna

Deployable hoop-column antennas have been employed extensively in communication satellites over the past few decades. The antenna may subject to significant deformation or even heat-induced vibration during on-orbit operation as a result of solar radiation shocks, which could potentially impact its normal functionality. In this paper, the finite element theory and Fourier thermal element method are combined to study the thermal–structural response of the antenna under solar thermal shock in a real space thermal environment. According to the antenna’s orbital position and orientation relative to the Sun and Earth’s, a novel spatial heat flux analysis model is first established to calculate the real solar heat radiation flux on local positions of the antenna considering the Earth’s shadow effect and reflector’s light shading effect. The coupled thermal–mechanical coupling analysis model which incorporates the cable pre-tension is then established and validated by comparison with the ground thermal radiation impact test. The on-orbit thermal–mechanical dynamic response of the antenna is examined during satellite operation in two types of orbits (geostationary orbit and general elliptical orbit). The findings indicate that the light-shadow effect intensifies the temperature gradient of the antenna and influences the thermal deformation of the antenna. However, due to the structural stability of the hoop-column antenna, minimal thermal vibration of the antenna is discerned.