Continuous variable speed pressure control method for sub-transonic flutter test
A control method and variable pressure technology, applied in aerodynamic testing, sustainable transportation, testing of machine/structural components, etc., can solve problems such as alarming air consumption, changes in dynamic characteristics of model structures, damage, etc., and achieve stable control methods. , The effect of saving air source and high control precision
Active Publication Date: 2022-04-29
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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Problems solved by technology
However, the shortcomings are also obvious. On the one hand, the air consumption of the high-speed temporary wind tunnel is proportional to the time. The longer the blowing time, the greater the air consumption, especially the speed-up pressure test, the air consumption is amazing; on the other hand If the blowing time is too long, the flutter test model is easily damaged due to fatigue even if flutter does not occur, resulting in changes in the dynamic characteristics of the model structure, and the required flutter characteristics cannot be obtained
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Embodiment 1
[0058] The test wind tunnel of this embodiment is a 0.6-meter high-speed wind tunnel. The wind tunnel is a three-sonic wind tunnel with temporary downflow of direct current. The cross-sectional size of the test section is 0.6m x 0.6m, the Mach number ranges from 0.4 to 4.5, and the attack angle ranges from -10° to 50°. like figure 2 As shown, the wind tunnel includes an antechamber 1, a test section 3, a supersonic diffusion section 6, and a suction ejector 7 connected sequentially from front to back. The rear end of the front chamber 1 is connected, the rear end of the 0# nozzle 2 is connected to the test section 3, the supersonic diffusion section 6 has four nodes from front to back, and the second node 5 of the super-expansion section is to adjust the cross-sectional area of the second throat key nodes.
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The invention belongs to the technical field of high-speed wind tunnel tests, and discloses a continuous variable speed pressure control method for a subsonic flutter test. According to the continuous variable speed pressure control method, the area of a second throat is changed by adjusting a second node of an adjusting sheet of a supersonic speed diffusion section, namely, the Mach number is controlled by dynamically adjusting the position of the second node of a super-expansion section, and the position adjustment of the second node of the super-expansion section is added into a wind tunnel test Mach number control program. The continuous variable-speed pressure control method for the sub-transonic-speed flutter test is stable, reliable and high in control precision, air sources are saved, the total pressure linear change rate is 0.5 kPa/se-2 kPa/se-2 kPa/se-2 under the continuous variable-speed pressure driving mode, the Mach number control precision is within the range of 0.002, and the continuous variable-speed pressure control method can be used for the sub-transonic-speed flutter test.
Description
technical field [0001] The invention belongs to the technical field of high-speed wind tunnel tests, and in particular relates to a continuously variable speed pressure control method for sub-transonic flutter tests. Background technique [0002] When carrying out conventional sub-transonic wind tunnel tests in high-speed temporary wind tunnels, the total pressure of the front chamber is adjusted through the main pressure regulating valve, and then the Mach number adjustment of the test section is realized. During the test, the total pressure of the front chamber and the reference The point static pressure ratio remains constant. The Mach number control accuracy in the test section is generally 0.003. The position of the regulator in the supersonic diffusion section of the wind tunnel is adjusted in place before the test blows, and does not participate in the flow field adjustment during the test. The control system of the supersonic diffusion section of the wind tunnel is ...
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IPC IPC(8): G01M9/04
CPCG01M9/04Y02T90/00
Inventor 荣祥森刘奇闫昱吴冠青康乐贾霜邓章林高鹏张长丰杨海滨张立波李腾骥
Owner INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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