High heat flow simulator for spacecraft vacuum heat tests

A vacuum thermal test and spacecraft technology, which is applied to the simulation device of space navigation conditions, aircraft component testing, space navigation equipment, etc., and can solve the problem of not being able to simulate the thermal environment

Inactive Publication Date: 2014-02-26
BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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Problems solved by technology

The high-temperature wind tunnel test can only assess the performance of the surface thermal pr

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  • High heat flow simulator for spacecraft vacuum heat tests
  • High heat flow simulator for spacecraft vacuum heat tests

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Embodiment Construction

[0017] The following is a specific implementation manner of the content of the present invention, and the content of the present invention will be further clarified through the specific implementation mode below. Of course, the following specific embodiments are described only to illustrate different aspects of the present invention, and should not be construed as limiting the scope of the present invention.

[0018] The structural diagram of the high temperature and high heat flow simulator used for the spacecraft vacuum thermal test in the space environment simulation chamber of the present invention is as follows figure 1 , figure 2 As shown, the high temperature and high heat flow simulator of the present invention mainly includes an infrared lamp array 6 high temperature heat insulation assembly unit 2, a mobile unit 3, a temperature measurement unit 7, a temperature control unit 8, and an infrared lamp belt in the infrared lamp array 6 There is a reflective screen, and...

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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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Application Information

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IPC IPC(8): B64F5/00B64F5/60B64G7/00
Inventor 王奕荣高庆华刘守文许忠旭裴一飞李振伟王洪兴张春莹
Owner BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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