Spacecraft high/low temperature separation testing system and method

The invention provides a spacecraft high/low temperature separation testing system and method, which are used to obtain the test parameters, when a first separation test piece and a second separation test piece are obtained. The system comprises a temperature test box for adjusting the environment temperature; a gravity balancing device for providing a balancing force for the separation test pieces; a detached body temperature control device for adjusting the temperature of each position of separation test pieces and simulating the in-orbit temperature distribution; a camera device for measuring the separation displacement and separation speed of separation test pieces during the separation process; a separation time measuring device for measuring the separation time of a separation mechanism; and a controller, which is used to control the unlocking separation of the separation mechanism, provide a synchronizing signal, and obtain the separation displacement, separation speed, and separation time, so as to calculate the relative speed, when a spacecraft is actually separated. The provided system and method are suitable for the separation tests of detached bodies with different sizes and weights. The test parameters are comprehensive, the precision is high, the operation is convenient, the efficiency is high, the adaptabitiy is strong, and the method and system are safe and reliable.