Remote and Feedback Control of the Flap Angle in a Wind Tunnel Test Model by Optical Measurement

Kazuhisa Chiba,Tatsuro Komatsu,Hiroyuki Kato,Kazuyuki Nakakita

doi:10.3390/aerospace7020011

Kazuhisa Chiba, Tatsuro Komatsu + Show 2 more

Open Access

https://doi.org/10.3390/aerospace7020011

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Abstract

We have developed a remote and precise feedback control system using optical measurement technology to alter the angle of a flap, which is part of a wind tunnel test model, automatically and to earn the aerodynamic data efficiently. To rectify the wasteful circumstance that Japan Aerospace Exploration Agency (JAXA)’s low-turbulence wind tunnel stops ventilation every time to switch model configurations, we repaired hardware for remote operation and generated software for feedback control. As a result, we have accomplished a system that dramatically advances the efficiency of wind tunnel tests. Moreover, the system was able to consider the deformation of the model through optical measurement; the system controlled flap angles with errors less than the minimum resolution of optical measurement equipment. Consequently, we successfully grasped the nonlinearity of three aerodynamic coefficients C L , C D , and C M p that was impossible so far.

Highlights

Aircraft wings optimized for cruise conditions provide control devices to ensure aerodynamic performance during takeoff and landing [1]
The first parameter is the pulse number of the stepping motors in the actuator; the second is the encoder value of the flap hinge line; the third is the 3D surface coordinates of the wind tunnel test model based on optical measurement
We describe the details of the wind tunnel test model, optical measurement equipment, and aerodynamic measurement equipment below

Summary

Introduction

Aircraft wings optimized for cruise conditions provide control devices to ensure aerodynamic performance during takeoff and landing [1]. Airbus has proposed the motorization of wind tunnel test models that can be remotely controlled [13]. The Boeing company has earned patents on the measurement technology of wind tunnel tests in the US [14]. We remotely manipulated an actuator to change model configurations sequentially without resting ventilation to enhance the efficiency of wind tunnel tests. An error results from the elastic deformation of wind tunnel models To minimize these errors is crucial to assure the exactitude of wind tunnel test data. The first parameter is the pulse number of the stepping motors in the actuator; the second is the encoder value of the flap hinge line; the third is the 3D surface coordinates of the wind tunnel test model based on optical measurement.

Feedback Control System Using Optical Measurement Technology

System Configuration

Wind Tunnel Test Model

Instruments for Optical Measurement

Instruments for Aerodynamic Measurement

Conclusions