Abstract: A composite design for the thermal management of an integrated star sensor on lunar orbit is proposed. On the lunar orbit, the thermal condition of the integrated star sensor is determined by the solar radiation, the infrared radiation of the lunar surface and the concentrated heat load of the star sensor. As the result, the thermal management of the star sensor is extremely difficult. The heat dissipation of the star sensor is realized through the combined actions of the heat pipe, the thermal control coating, the MLI and the electric heater. The thermal simulation is performed to verify the design. The result shows that the maximum temperature of the star sensor is 36.7℃, which satisfies the temperature requirement of the star sensor.