Abstract: To study the comprehensive thermal effects of the flight attitude, the external thermal flux, the plume parameters of the core module engine, and the thermal control coatings outside the antenna on the antenna temperature, a thermal analysis is conducted under two low- temperature conditions and six high-temperature conditions to validate the thermal design. It is shown that under the low temperature conditions, the minimum temperature of the space frame antenna in the inertial flight mode is lower than that in the forward flight mode, while the minimum temperature of the multi-layer surface on the deployable manipulator is -85 ℃, which meets the requirements of the thermal control. Under the high temperature conditions, the antenna temperature in the inertial flight mode is higher than that in the forward flight mode; the thermal effect caused by the plume of the orbit control thruster is greater than that caused by the yaw thruster. When the internal and external surfaces of the communication antenna are coated with the ACR-1 white paint, and with one time plume heat flux density of the orbit control thrusters, the maximum temperature of the antenna is 123 ℃, not exceeding the requirements for the usage.