The invention discloses a steady test
system and method for heat conduction coefficient and interface
thermal resistance of a
radiation heat-dissipation correction-type
aviation background material. The device comprises a
germanium solar absorption panel hot source, a
radiation refrigerating plate cold source, a temperature test
system and a
data acquisition system, wherein the hot source and thecold source both are connected with a segment of cylindrical
aviation aluminum-
alloy material, a high-accuracy temperature sensor is arranged at an upper side of the aluminum-
alloy material and is used for testing a temperature, the cold source, the hot source and a heat conductor connected with the cold source and the hot source can be maintained coaxially on a mechanical structure, a
cold side is fixed, a hot side can axially move,
radiation-prevention
layers are arranged at outer sides of an aluminum-
alloy heat conductor and a sample placement part, radiation-prevention
layers are additionally arranged outside a temperature
data acquisition device, the temperature sensor and a connection wire, and power is supplied to the acquisition device by a
solar cell. The hot source and the radiation refrigerating panel cold source can stably work for a long time in a
space environment, the system can be enabled to be adaptive to the
space environment with the application of the
aviation aluminum-alloy material, and the radiation heat dissipation of the test system in the
space environment is isolated by the radiation-prevention
layers.