Calibration method of response time of pressure-sensitive paint based on non-electric nonel-driven shock tube
A calibration method and response time technology, applied in the field of wind tunnel testing, can solve problems such as complex structure, high construction and maintenance costs
Active Publication Date: 2021-03-16
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
[0049] 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.
[0050] 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 method for calibrating the response time of a pressure-sensitive paint based on a shock tube driven by a non-electric detonator. This calibration method uses a special calibration device, and uses the shock wave generated by the explosion of the nonelectric nonel tube to provide a pressure step. It includes the following steps: power on the excitation light source, photomultiplier tube and oscilloscope; turn on the excitation gun to excite the nonelectric detonator to explode; use the photomultiplier tube to record the change of the luminous intensity of the pressure-sensitive paint coating; use the oscilloscope to simultaneously display and record the dynamic pressure The pressure change curve measured by the sensor and the time-varying curve of the luminous intensity of the pressure-sensitive paint coating measured by the photomultiplier tube; the time when the luminous intensity value of the pressure-sensitive paint coating reaches 99% of the stable luminous intensity of the pressure step is taken as the pressure Sensitive paint response time, complete the calibration. The calibration method is simple, safe and reliable, and has strong practicability, which can greatly reduce the experimental cost of the pressure-sensitive paint response time calibration 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 method for calibrating the response time of pressure-sensitive paint 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 198...
Claims
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IPC IPC(8): G01L27/00G01M9/06
CPCG01L27/00G01M9/06
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