High heat flow simulator for spacecraft vacuum heat tests

Abstract

The invention discloses a high-temperature high heat flow simulator for spacecraft vacuum heat tests in a space environment simulating chamber. The simulator mainly comprises infrared light arrays, a high-temperature insulation component unit, moving units, a temperature measuring unit and a temperature controlling unit. A plurality of infrared lights in the infrared light arrays are provided with reflective screens, the infrared lights are arrayed and combined to form the infrared light arrays according to requirements of heat flux density and uniformity, baffles surround the periphery of the infrared light arrays, high-temperature multi-layer insulation components are mounted among the infrared lights, a mounting baseplate and the baffles, and a high temperature region is limited in region formed through specimen irradiated face and the infrared light array high-temperature insulation components. According to the high-temperature high heat flow simulator, by means of unique design of the infrared light arrays and the high-temperature insulation components, technical difficulties of high-temperature high heat flow simulation when vacuum heat tests are performed on a spacecraft are solved, high-temperature high heat flow space environment can be simulated when vacuum heat tests are performed on spacecrafts in series of deep space exploration and space shuttles, and the spacecrafts can be tested.

Description

technical field [0001] The invention belongs to the field of space vehicle ground vacuum heat test. Specifically, the invention relates to a thermal simulation system for high temperature and high heat flow vacuum heat test of a space vehicle and its components on the ground. Thermal matching, heat resistance and other properties of the structure. Background technique [0002] The spacecraft thermal vacuum test is a test to verify various performances and functions of the spacecraft under specified vacuum and thermal cycle conditions. It is one of the important tests in the multi-environmental simulation tests in the development stage of the spacecraft. The main purpose of the test is to expose the spacecraft’s material and manufacturing process defects under vacuum and thermal cycle conditions, and eliminate early failures, thereby greatly improving the reliability of the spacecraft’s in-orbit operation. [0003] In the spacecraft thermal vacuum test, in addition to simul...

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Problems solved by technology

The high-temperature wind tunnel test can only assess the performance of the surface thermal protection material, and cannot simulate the thermal environment of the cabin load during re-entry

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