研究目的
To design, fabricate, and test a low profile fibre optic sensing tape for monitoring variations in pressure on aircraft wings.
研究成果
The wind tunnel data indicates the fibre optic sensors are able to accurately monitor pressure profiles across an airfoil. The sensors used in this instance had an average thickness of 1.5 mm and so, due to the size of the scale model, the 3D printed section included a recess to allow the surface of the sensors to remain flush with the surface of the wing.
研究不足
The effect of the height of the sensor array on full size wings will be considerably less and it will be possible to surface mount the sensor parallel to the airfoil chord without unduly affecting the pressure profiles.
1：Experimental Design and Method Selection:
The sensor tape was fabricated using a pair of ‘Draw Tower Grating’ (DTG) arrays each containing 6 discrete FBG sensing elements. The FBG elements were written at 10 mm intervals along two separate single mode optical fibres.
2：Sample Selection and Data Sources:
The sensor array was bonded to a 3D printed wing based on a NACA 0024 profile.
3：List of Experimental Equipment and Materials:
Standard off the shelf optical interrogators (FBG Scan 804D, FBGS International, Jena, Germany) and readily available fibre optic arrays.
4：Experimental Procedures and Operational Workflow:
The instrumented airfoil was mounted vertically on a rotary table in the wind tunnel. Data was collected from both the pressure taps and the fibre optic sensing array as the wind speed was varied between 15 and 25 m/s and the Angle of Attack (AoA) was varied between ±10 degrees.
5：Data Analysis Methods:
The data from the pressure taps and the fibre optic sensing array were recorded at 500 Hz with a 100 point rolling average to give an effective data rate of 10 Hz to reduce high frequency noise.
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