Response measurement method for aircraft model in wind tunnel

Abstract

The invention provides a response measurement method for an aircraft model in a wind tunnel. The method comprises the steps: pasting marking points on an aircraft wind tunnel model, employing a high-speed camera for continuously recording a video, directly observing buffeting and flutter frequencies under the conditions of micro vibration, high-frequency vibration and large amplitude through a micro motion amplification algorithm, further carrying out the optical flow calculation on the amplified video, and measuring an attack angle; enabling the Mach number to remain as a constant, rotating the aircraft model to enable the attack angle to change continuously in a large range, if the pulsation frequency and the amplitude in attack angle measurement data are suddenly changed, determining that the suddenly changed angle is the initial attack angle of buffeting, and the corresponding lift coefficient is the initial lift coefficient of buffeting; after buffeting occurs, performing signal enhancement and filtering on the mark points on the aircraft model by using a micro motion amplification algorithm, so non-contact measurement and extraction of vibration signals can be realized. The method has the advantages of being high in reliability and precision, free of contact, easy to implement and the like.

Description

technical field [0001] The invention belongs to the technical field of non-contact measurement, in particular to a method for measuring the response of an aircraft model in a wind tunnel. Background technique [0002] Many aerodynamic parameters are required in the design and development of aircraft, and these parameters are mainly obtained by testing the scaled model of the aircraft in a wind tunnel. Therefore, people simulate the airflow distribution when the aircraft is flying in the wind tunnel. The attitude of the aircraft test model in the wind tunnel during the blowing test includes the basic data of the wind tunnel test such as the model's angle of attack, sideslip angle, and roll angle. Dynamic, real-time, and accurate acquisition of model attitude angle data under blowing conditions is of great significance for wind tunnel tests. [0003] In the existing wind tunnel tests, acceleration sensors, laser displacement meters, etc. are generally used to measure the res...

AI Technical Summary

Problems solved by technology

However, when the wind speed does not reach the critical point of flutter and buffeting, the vibration of the wing and fuselage is a slight vibration and the vibration frequency is relatively fast

The human eye has limited time resolution and spatial resolution, in this case, it is impossible to identify the overall vibration state of the aircraft in the wind tunnel

Even if a high-speed camera is used to record relatively fast micro-vibrations, the spatial resolution of the human eye limits the direct observation of machine vibrations

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