Shutter type rotatable infrared heating cage

Abstract

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.

Description

technical field [0001] The invention belongs to the technical field of spacecraft ground thermal tests, and in particular relates to a rotatable infrared heat flow simulation system for spacecraft thermal tests in a vacuum and low temperature environment. Background technique [0002] Before the spacecraft is launched, it is necessary to conduct a space environment simulation test on the spacecraft on the ground to verify the reliability of the spacecraft's in-orbit operation, and the vacuum thermal test is an important part of the spacecraft environmental test. In the vacuum thermal environment test, the infrared cage is an effective means of simulating the external heat flow. The infrared cage is generally arranged 100mm-200mm outside the spacecraft, and its shape generally changes with the outer envelope of the spacecraft. [0003] The infrared cage is generally composed of strips and a skeleton. The skeleton is arranged according to the outer envelope of the spacecraft. ...

AI Technical Summary

Problems solved by technology

During the vacuum thermal test, the infrared cage is installed on the surface of the spacecraft to form a closed outer envelope. Since the strips have a certain width and surround the surface of the spacecraft with a certain coverage (0.1-0.5), this part of the strips The existence of the radiative heat exchange between the spacecraft and the heat sink is blocked, especially under low temperature conditions, which seriously affects the cooling rate of the spacecraft and prolongs the test time of the spacecraft

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