Wind tunnel testing model supporting mechanism based on parallelogram mechanism
A parallelogram and wind tunnel test technology, which is applied in the testing of machine/structural components, aerodynamic tests, measuring devices, etc., can solve problems affecting the effect of aircraft models, affecting the quality or success of aircraft development, and achieve reasonable structure, Improvement effect, effect of large range of motion
Active Publication Date: 2015-03-25
YANGZHOU UNIV
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Problems solved by technology
The performance of the model support mechanism for the wind tunnel test of the aircraft model directly affects the effect of the wind tunnel test of the aircraft model, thereby affecting the quality or success of the aircraft development
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Embodiment Construction
[0018] The present invention will be further described below in conjunction with accompanying drawing.
[0019] A wind tunnel test model support mechanism based on a parallelogram mechanism, consisting of a base 1, a rotating servo motor 2, a rotating rod 3, a swinging servo motor 4, a swinging rod one 5, a swinging rod two 6, a swinging rod three 7, and a swinging rod four 8. Rolling servo motor 9, rolling fixed bracket 10, model support rod 11, aircraft model 12, etc. are installed and connected. The rotating servo motor is fixed on the base, and the rotating rod is fixed on the motor shaft of the rotating servo motor to form a rotating mechanism. The rotating rod is perpendicular to the base, and the rotating servo motor drives the rotating rod to rotate 360 degrees around its axis; one end of swinging rod 1, swinging rod 2, swinging rod 3 and swinging rod 4 are respectively connected by rotating pairs to form a parallelogram four-bar linkage mechanism, The other ends of ...
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The invention relates to a wind tunnel model testing supporting mechanism based on a parallelogram mechanism, and belongs to the technical field of aircraft development testing equipment. The wind tunnel testing model supporting mechanism is composed of a base, a rotating servo motor, a rotating rod, an oscillating servo motor, a first oscillating rod, a second oscillating rod, a third oscillating rod, a fourth oscillating rod, a rolling servo motor, a rolling fixed support, a model supporting rod and an aircraft model. The rotating servo motor, the oscillating servo motor and the rolling servo motor drive a control rotating mechanism, an oscillating rotating mechanism and a rolling mechanism, the aircraft model is guided by the mechanisms to conduct three-dimensional motion around a virtual center, and the three-freedom-degree yaw motion, pitching motion and rolling motion of the aircraft model are achieved. According to the wind tunnel testing model supporting mechanism, it is ensured that the aircraft model can have large enough motion range, the aircraft model is guided through the mechanisms to keep the mass center of the itself unchanged, the requirement of the aircraft model for wind tunnel testing is met, and the wind tunnel testing effect of the aircraft model is improved.
Description
technical field [0001] The invention relates to an aircraft model support mechanism for an aircraft to carry out wind tunnel tests, in particular to the structure of a wind tunnel test model support mechanism capable of guiding an aircraft model to realize three-dimensional rotation around a virtual center, and belongs to the technical field of aircraft development and test equipment. Background technique [0002] Wind tunnel test is an essential link in the development of aircraft. The development of each aircraft requires a large number of experiments in the wind tunnel. The wind tunnel test of aircraft is inseparable from the model support system. The performance of the model supporting mechanism for the wind tunnel test of the aircraft model directly affects the effect of the wind tunnel test of the aircraft model, thereby affecting the quality or success of the aircraft development. Contents of the invention [0003] The purpose of the present invention is exactly to ...
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IPC IPC(8): G01M9/04G01M9/08
Inventor 陈文家邵子宴李鹭扬胡勇金李关键
Owner YANGZHOU UNIV