Response time calibration device for pressure-sensitive paint based on non-electric nonel-driven shock tube
A calibration device and response time technology, applied in the field of wind tunnel testing, can solve the problems of complex structure, high construction and maintenance costs, etc., and achieve the effects of good transmission performance, safety, reliability, practicability, and strong safety and reliability.
Active Publication Date: 2021-04-06
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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Problems solved by technology
Conventional high-pressure gas-driven shock tubes are relatively complex in structure, requiring high-pressure gas sources and fast valves and other supporting devices, and the construction and maintenance costs are relatively high
Method used
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Embodiment 1
[0039]The nonelectric nonel tube 1 in this embodiment is a nonelectric hose whose inner wall is coated with mixed explosive powder (a mixture of explosive and metal powder). The proportion is 91% of RDX, 9% of aluminum powder and other components, and the coating dosage is 14mg / m~16mg / m.
[0040] The shock tube 2 is processed, and the nonelectric nonel 1 and the shock tube 2 are connected by a nonel fixing device 3 . The nonel fixing device 3 is an aluminum rectangular parallelepiped metal block of 22mm (width) × 22mm (height) × 200mm (length), and the central axis has a through hole with a diameter of 3mm. Insert the nonelectric nonel tube 1 into the through hole of the nonel fixing device 3, the inlet end is connected with a special excitation gun, and the outlet end is flush with the tail end surface of the nonel fixing device 3. The length of the nonelectric nonel 1 is 250 mm to 1000 mm, and three M3 threaded through holes are provided every 50 mm on the side wall of the ...
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Abstract
The invention discloses a pressure-sensitive paint response time calibration device based on a shock tube driven by a non-electric detonator. The calibration device includes a shock tube driven by a non-electric detonator connected to the excitation gun at the front end; symmetrical optical windows installed on both sides of the rear section of the shock tube; sprayed on the inner tail surface of the shock tube pressure-sensitive paint coating; located outside one optical window, an excitation light source that matches the incident wavelength of the pressure-sensitive paint; located outside the other optical window, a photomultiplier tube used to record changes in the luminous intensity of the pressure-sensitive paint coating; located outside the excitation The end of the wave tube is a dynamic pressure sensor used to record the pressure step change process of the end surface of the shock tube; and an oscilloscope connected to the dynamic pressure sensor and the photomultiplier tube. The calibration device has the advantages of simple structure, stable performance, safety, reliability and high practicability, which can greatly reduce the experimental cost of calibrating the response time of the pressure-sensitive paint and improve the experimental efficiency.
Description
technical field [0001] The invention belongs to the technical field of wind tunnel tests, and in particular relates to a pressure-sensitive paint response time calibration device based on a nonelectric nonel-driven shock tube. Background technique [0002] The traditional measurement method of unsteady pressure distribution in aircraft wind tunnel test is to install dynamic pressure sensors at the measurement points on the surface of the test model. This method can only obtain the pressure of discrete points on the surface of the test model, and the selection of measurement points is also limited by the structure of the test model. Layout, some locations simply do not have space to install dynamic pressure sensors. At the same time, the test model design and manufacture, test preparation and other links are relatively complicated. [0003] Pressure Sensitive Paint (PSP) optical measurement technology is a non-contact measurement technology developed after the 1980s and appl...
Claims
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IPC IPC(8): G01L25/00G01M9/06
CPCG01L25/00G01M9/06
Inventor 李国帅熊健王元靖何彬华黄辉王红彪刘祥
Owner INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT