Abstract: In view of the difficulty of the desirable temperature control in the spacecraft component test due to the non-uniform thermal field and the limited coverage of the single point control, this paper studies the uniformity of the thermal field, the temperature distribution?law on different faces of the component inside the test chamber, and various factors that affect the distribution. With the test method for the temperature measurement and control with the multiple temperature measurement and control system, the method of choosing the temperature control point in the test is determined, therefore,?the control of?temperature may be kept in the local areas in the thermal test.