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Air inlet test simulation device and simulation method
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A technology of simulation device and simulation method, applied in the field of wind tunnel test, can solve the problems of poor test data quality and low test efficiency, etc.
Active Publication Date: 2021-04-20
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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[0005] The purpose of the present invention is to provide an air inlet test simulation device and simulation method, aiming to solve the technical problems of poor test data quality and low test efficiency existing in the prior art
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Embodiment 1
[0036] Such as figure 2 Shown is a schematic diagram of an inlet test simulation device in Embodiment 1 of the present invention, which includes: a model support assembly 10, a model support rod 11, a model 20, a flow simulator 30, a simulator support assembly 40, a flexible suction An air pipe 50, wherein the model support assembly 10 is connected to the outer periphery of the model 20 through the model support rod 11;
[0037] One end of the flexible suction pipe 50 is connected to the air outlet of the model 20, and the other end of the flexible suction pipe 50 is connected to the air inlet of the flow simulator 30;
[0038] The flow simulator 30 is supported on the simulator support assembly 40 , and the simulator support assembly 40 can be adaptively adjusted along with the adjustment of the model support assembly 10 .
[0039] When performing the intake port test simulation, the flow rate of the intake port of the model 20 is simulated by the flow simulator 30 .
[00...
Embodiment 2
[0049] Such as Figure 4 Shown is a schematic diagram of an inlet test simulation method in Embodiment 2 of the present invention, which includes the following steps:
[0050] Step S10: arranging the above-mentioned inlet test simulation device in the wind tunnel test section;
[0051] Step S20: adjusting the model 20 so that the attitude angle of the model 20 meets the test requirements;
[0052] Step S30: Make the simulator support assembly 40 follow the movement;
[0053] Step S40: Carry out the air inlet test simulation.
[0054] Further, the step S20 adjusts the model 20 in the following manner: the model support assembly 10 drives the model 20 to move in X, Y, Z directions and rotate around the Y direction through the model support rod 11 .
[0055] Further, the step S30 enables the simulator support assembly 40 to follow the movement in the following manner: the mobile support base 41 follows the movement in the Y and Z directions, the slider 43, the sliding connecti...
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Abstract
The invention is suitable for the technical field of wind tunnel tests, and provides an air inlet channel test simulation device and simulation method, the air inlet channel test simulation device comprises a model support assembly, a model support rod, a model, a flow simulator, a simulator support assembly and a flexible air suction pipe, and the model support assembly is connected with the peripheral part of the model through the model support rod; one end of the flexible air suction pipe is connected with an air outlet of the model, and the other end of the flexible air suction pipe is connected with an air inlet of the flow simulator; the flow simulator is supported on the simulator supporting assembly, and the simulator supporting assembly can be adjusted in a self-adaptive mode along with adjustment of the model supporting assembly. According to the invention, the test data quality and the test efficiency can be improved.
Description
technical field [0001] The invention belongs to the technical field of wind tunnel tests, in particular to an air inlet test simulation device and a simulation method. Background technique [0002] In the low-speed wind tunnel aircraft inlet performance test, it is a key technical link to accurately simulate the flow of the inlet; among them, in the low-speed wind tunnel without a vacuum suction system, the injection flow simulator is usually used. The injection action is used to simulate the flow of the intake port. Such as figure 1 Shown is the inlet test simulation device in the prior art. This method is disclosed in the document "Optimized Design of Cylindrical Distributed Ejector for Low-speed Wind Tunnel Inlet Test, Wu Chaojun et al., Journal of Aerodynamics". During this method, the model 1' is fixed in the wind tunnel test section by a support device 2' that can change the angle of attack and sideslip angle, and the high-speed airflow ejected to ensure that the jet...
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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/04G01M9/06G01M9/08
Inventor 巫朝君李东徐彬彬陈陆军汪军付华孙福振
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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