On-Orbit Dynamic Performance Analysis of a Large Deployed Circular Truss Antenna Structure Based on Two Thermal–Structural Coupling Dynamic Models

Abstract Deployable satellite antenna structure has a bright prospect in high power space-borne antennas for strict telecommunication tasks. The alternating hot and cold environment in space as well as the nonuniform distribution of temperature may cause severe thermal-induced vibration problem for such a large-size and high flexible structure. In this work, a novel spatial orbital solar radiation model is presented with consideration of both the shielding effect of sunlight between antenna components and the earth shadow effect. Based on this model, a one-dimensional thermal–mechanical coupling dynamic model (ODT-MCDM) and three-dimensional one (TDT-MCDM) are, respectively, established to perform thermal–mechanical dynamic analysis of a deployable satellite antenna during orbital operation for comparison. A one-dimensional thermal conductive model and a Fourier thermal conductive model are, respectively, included in these two thermal–mechanical coupling dynamic models for heat conduction calculation. Temperature field variations and dynamic deformations of an example deployable circular truss antenna during on-orbit operation are examined using the established two thermal–mechanical coupling dynamic models. It is demonstrated that the antenna structure has similar temperature distribution when the one-dimensional thermal conductive model and Fourier thermal conductive model are used, but the temperature difference is lower when the latter one is used. What is more, only the three-dimensional thermal–mechanical coupling dynamic model can capture the high frequency vibration due to circumferential temperature gradient induced bending moment.