A device for an ultra-micro-sized aircraft wind tunnel test bench

Abstract

The invention provides an ultramicro-size aircraft wind tunnel experiment table device, and the device comprises an integrated aircraft experiment frame, an experiment segment, an experiment segment support, rectification grids, CPU adjustable tachometers, CPU adjustable tachometer fixing frames, a guide rail and a miniature aircraft, wherein the integrated aircraft experiment frame contacts with three rectification grids. The integrated aircraft experiment frame contacts with the experiment segment support. The integrated aircraft experiment frame contacts with two CPU adjustable tachometer fixing frames. The two CPU adjustable tachometer fixing frames respectively contact with two CPU adjustable tachometers, and enable the two CPU adjustable tachometers to be fixed. The experiment segment support contacts with the experiment segment, and enables the experiment segment to be fixed. The interior of the experiment segment is provided with the guide rail. The miniature aircraft is disposed on the guide rail. The device achieves the design of an experiment device for a miniature wind tunnel, achieves the aerodynamic measurement of a miniature aircraft, and achieves the detection of relation between the beat frequency and flow field of a small plane.

Description

technical field [0001] The invention relates to the field of miniature wind tunnel experiments, in particular to a device for an ultramicro-sized aircraft wind tunnel test bench. Background technique [0002] The wind tunnel is a very important method and link in the development of aircraft. In order to understand the flight characteristics and aerodynamic characteristics of the aircraft, it is generally necessary to conduct a large number of wind tunnel experiments on the aircraft. The aircraft is placed in the flow field of the wind tunnel test bench for testing. In traditional wind tunnel experiments, a certain part of the aircraft is generally tested. The test objects are generally test models, which are supported by special brackets for experiments. [0003] Retrieve some documents, such as Chinese utility model patent 201220024203.0, which discloses a parallel flexible cable traction mechanism applied to aircraft wind tunnel tests: "multiple points on the aircraft mo...

AI Technical Summary

Problems solved by technology

This utility model patent uses flexible cable traction to replace the traditional bracket, which minimizes the impact on the air flow field, and makes it easier to change the attitude of the aircraft model, making the wind tunnel test data of the aircraft model closer to reality.” However, compared with the traditional Like the wind tunnel test, the aircraft object of the wind tunnel test of this patent is generally a test model, which is still different from the wind tunnel test of a real aircraft; in addition, although this structure reduces the influence on the air flow field, this complex The flexible cable structure is not suitable for wind tunnel tests of micro-aircraft, and the error will be relatively large. This structure cannot solve the relationship between the flow velocity of the airflow and the flapping frequency of the wings of the aircraft.

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