Abstract: Large space membrane antennas offer advantages in terms of light weight and large folding-to-deployment ratios, making them an important direction for the development of space deployable antennas. However, when membrane antennas enter and exit the Earth’s shadow area, they experience rapid changes in thermal radiation that cause thermal deformation and thermally induced vibrations, which can affect their performances. This paper is based on the theories of heat transfer and structural dynamics, and uses NX and ANSYS software to establish a thermal induced vibration model for thermal induced vibrations in large space membrane antennas, analyzing temperature field changes, thermal induced vibrations, and the factors influencing these vibrations when entering the earth's shadow area. Research has shown that the size and damping of antenna structures, prestressing of tension ropes, and material parameters of thin film arrays have a significant impact on the thermal induced vibration of large membrane antennas. By carefully selecting appropriate structural and material parameters, thermal induced vibrations can be effectively suppressed, providing important reference and support for the design for large space membrane antennas and suppression of thermal induced vibration.