Introduction:

Thermal vacuum testing refers to the verification of various performance and functions of spacecraft and their components under vacuum and specific temperature conditions, consisting of cold soak, hot soak, and temperature transition processes.

Test Parameters:

1. Maximum internal effective dimensions < ?3.5m × 5.5m;

2. Pressure range: (1×10??Pa to 1.01×10?Pa);

3. Heat sink temperature ≤ 100 K;

4. Temperature range: -150℃ to +60℃;

5. Not measured: Solar simulation;

Version/Standard No.: GJB 1027A-2005 6.2.8, 6.2.9, 6.4.4, 7.2.7, 7.2.8, 7.4.3

Standard Name: Test Requirements for Launch Vehicles, Upper Stages, and Spacecraft

Standard Type: National Standard