The invention discloses a rotatable shutter type infrared cage used in a vacuum heat test process of a spacecraft. The rotatable shutter type infrared cage mainly comprises an infrared cage main framework, a gear motor, a coupling, connecting rods, pin shafts, heating assemblies, bearings, bearing seats, and an angle sensor, wherein a motor mounting seat of the gear motor is arranged on the side surface of the main framework; an output shaft of the gear motor on the motor mounting seat is coaxially connected with one of infrared heating units through the elastic coupling; a plurality of infrared heating units are connected through the connecting rods in parallel connection and are separately fixed through the pin shafts; when the connecting rods in parallel connection, the pin shafts and the heating units are combined together, all the heating units can form a parallel connection mechanism, and under the action of the connecting rods in parallel connection, the heating units synchronously rotate. During simulation of low-temperature environment, the heating units rotate through driving units, so that heating tapes rotate by 90 degrees, heating tape surfaces are vertical to the surface of the spacecraft, the shielding of heating tape strips to the spacecraft is reduced, the area of the spacecraft relative to heat sink radiation is enlarged, and the temperature falling rate of the spacecraft is increased.