Heating system for simulating high-temperature and high-heat-flow environment on ground

An environmental simulation and heating system technology, applied in the field of high temperature and high heat flow simulation test heating system, can solve the problems of slow system response, complex structure design, not suitable for rapid temperature rise and fall test, etc., to achieve high heating power, flexible configuration, Excellent control performance

Inactive Publication Date: 2019-08-16
BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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Problems solved by technology

Silicon-molybdenum rods and graphite heaters can obtain higher test temperature and heating heat flow, but the structure

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  • Heating system for simulating high-temperature and high-heat-flow environment on ground
  • Heating system for simulating high-temperature and high-heat-flow environment on ground

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[0022] 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.

[0023] figure 1 Shown is a system working principle diagram of a heating system for simulating ground high temperature and high heat flow environment according to the present invention. The system includes an infrared light array 1; a branch junction box 2; a power supply cable 3; a power control system (that is, a power adjustment device) 4; a data acquisition device 5; pipeline 9; water outlet collector 10; host computer 11. The data acquisition device 5 collects the heat flow value of the water-cooled high-temperature heat flow meter installed on the surface of the ...

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Abstract

The invention discloses a heating system for simulating the high-temperature and high-heat-flow environment on the ground. The heating system includes a U-shaped infrared lamp array, a water-cooled reflection module, a cooling water system, a power control system, a lamp array branch wire junction box, an upper computer and data acquisition equipment, the data acquisition equipment collects a heatflow value and a temperature value, the upper computer obtains a current value output by the power control system through the values, the power control system outputs the specified current value to supply power to the U-shaped infrared lamp array, the U-shaped infrared lamp array heats a specimen by means of thermal radiation and thermal convection, and the cooling water system flows through thewater-cooled reflection module to keep the temperature of each U-shaped infrared lamp within the normal working temperature range. The heating system can be used for high-temperature and high-heat-flow simulation testing under various environments such as the atmospheric environment, the vacuum environment, the vacuum low-temperature environment and the low-air-pressure environment.

Description

technical field [0001] The invention belongs to the technical field of ground heat tests of spacecraft and other aircraft, and in particular relates to a heating system for high-temperature and high-heat flow simulation tests of spacecraft in various environments such as atmospheric environment, vacuum environment, vacuum low-temperature environment, and low-pressure environment. Background technique [0002] During the reentry process of a spacecraft or aircraft, the flight Mach number is large, and the surface of the thermal protection system is subjected to different degrees of aerodynamic heating. The reliability of the thermal protection system is a key factor for flight safety. The harsh environment of pneumatic heating has a series of adverse effects on structures and materials. The coupling of force / thermal loads such as extreme surface temperature, large temperature gradient, and high noise pulsating pressure are notable characteristics of its flight orbit cycle env...

Claims

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Application Information

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IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 王晶柳晓宁简亚彬冯尧杨晓宁安万庆周艳朱熙王奕荣
Owner BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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