1400°C high temperature thermal-mechanical coupling test device for the airfoil structure of hypersonic aircraft

A hypersonic, structural testing technology, applied in the testing of machines/structural components, measuring devices, instruments, etc., can solve problems such as deformation, high temperature softening, etc., to achieve the effect of convenient use, safe and reliable connection and use, and simple structure of the device

Inactive Publication Date: 2011-11-30
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0006] The technical solution of the present invention is to overcome the deficiencies of the prior art and provide a 1400°C high-temperature thermomechanical coupling test device for the airfoil structure of a hypersonic aircraft. The problem of high-temperature softening and deformation of the ...

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  • 1400°C high temperature thermal-mechanical coupling test device for the airfoil structure of hypersonic aircraft
  • 1400°C high temperature thermal-mechanical coupling test device for the airfoil structure of hypersonic aircraft
  • 1400°C high temperature thermal-mechanical coupling test device for the airfoil structure of hypersonic aircraft

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Embodiment Construction

[0017] Such as figure 1 As shown, the present invention consists of a hypersonic vehicle airfoil structure test piece 1, fastening bolts 2, L-shaped fixed support 3, silicon-molybdenum heating array 4, high-temperature fastening bolts 5, water-cooled metal loading assembly 6, U-shaped water-cooled Channel 7, connecting support 8, water inlet 9, water outlet 10, force sensor 11, hydraulic actuator 12, loading coupling rod 13, temperature sensor 14, computer 15 and heat insulation baffle 16.

[0018] The hypersonic vehicle airfoil structure test piece 1 is fixed on the L-shaped fixed support 3 by fastening bolts 2 to form a cantilever structure. A row of infrared radiation silicon-molybdenum heating arrays 4 capable of generating a high temperature environment of 1400°C is arranged at a distance of about 50 mm from the upper and lower surfaces of the hypersonic aircraft wing structure test piece 1, to provide the upper and lower surfaces of the hypersonic aircraft wing structure...

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Abstract

The invention discloses a 1400-DEG C high-temperature thermal-mechanical coupling test device for the aerofoil structure of a hypersonic vehicle, which comprises a test sample of the aerofoil structure of the hypersonic vehicle, a silicon-molybdenum heating array, a water-cooled metal-loading component, a U-shaped water-cooled channel, a force sensor, a hydraulic actuator, a temperature sensor and a computer. Because the water-cooled metal-loading component is designed into a U-shaped hollow structure, the problems of high-temperature softening and deformation existing in the metal-loading component at 1400 DEG C are solved by using a method of cooling the inside of the metal loaded component with flowing liquid, the high-temperature (up to 1400 DEG C) thermal-mechanical coupling test on the aerofoil structure can be realized, and the ultimate strength of the aerofoil structure in high-temperature thermal-mechanical complex environment and other important parameters can be obtained, thereby providing a reliable basis for the safety design of a hypersonic vehicle structure in high-speed, high-temperature thermal-mechanical coupling environments.

Description

technical field [0001] The invention relates to a 1400°C high-temperature thermomechanical coupling test device for the airfoil structure of a hypersonic aircraft, especially when performing the aerodynamic and thermal environment test simulation of the airfoil structure of a hypersonic aircraft, the test device can measure the airfoil at a temperature as high as 1400°C Important parameters such as the thermal strength limit of the structure provide an important basis for the thermal strength design of the hypersonic vehicle structure in an extreme high-temperature thermodynamic composite environment. Background technique [0002] With the development of aerospace technology, the design flight speed of long-range maneuvering aircraft is constantly increasing. At the same time, the combat performance requirements of high-speed, high-precision, and high-maneuverability aircraft in modern warfare have caused countries all over the world to compete to develop hypersonic aircraft...

Claims

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Application Information

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IPC IPC(8): G01N25/00G01M13/00
Inventor 吴大方潘兵吴爽宋凯
Owner BEIHANG UNIV
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