In order to solve the thermal control problem of multiple optical remote sensing payloads and platform units on asatellite using limited thermal control resources, a design scheme based on active and passivethermal control strategies was presented. First, according to the satellite characteristics, thermal control requirements, and orbital heat flux, the thermal designing overall project was confirmed. Next, detailed thermal design instructions foroptical payloads and important platform instruments were listed, and the temperaturesof satellite subassemblies are calculated by finite element analysis software. Then, a thermal balance experiment on the whole satellite system was carried out to obtain test temperatures and verify the correctness of the thermal design. Finally, the real effect of the thermal design scheme was proved by comparing the temperature data obtained from on-orbit telemetry, thermal analysis, and thermal testing of the satellite. On-orbit telemetry data indicate that the temperature of the main payload camera is controlled from 19.7 ℃ to 20.3 ℃.The temperature of minor optical payloads ranged from -31.2 ℃ to 6.6 ℃,and the temperature of units inside the satellite cabinranged from 9.7 °C to 29.5 ℃. All the temperature results meet the requirements of the thermal control index. The temperature difference between on-orbit telemetry, thermal analysis, and thermal testing is less than ±3 ℃.The results show that the thermal design of the optical remote sensing satellite is correct and feasible, while the thermal analysis and test process are reasonable and credible.