Videogrammetric Model Deformation Measurement Technique for Wind Tunnel Applications

Barrows, Danny A.

doi:10.2514/6.2007-1163

Cited by 33 publications

(18 citation statements)

References 10 publications

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“…There are many articles about aerodynamic deformation measurement for wing models and MAVs using a wind tunnel [8] [9]. However, the measurement Journal of Flow Control, Measurement & Visualization of the meter-scale, entire shape, actual UAV is very few.…”

Section: Introductionmentioning

confidence: 99%

Wind Tunnel Test for Videogrammetric Deformation Measurement of UAV for Mars Airplane Balloon Experiment-1 (MABE-1)

Fujita¹,

Oyama²,

Kubo³

et al. 2019

JFCMV

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This paper reports the results of the aerodynamic deformation measurements of the meter-scale, entire shape, actual UAV in the wind tunnel using a video grammetry technique. The measured airplane was the airplane for Mars exploration being developed by Japan Aerospace Exploration Agency (JAXA) and Japanese universities. Its main wing span length was 2.4 m. The video grammetry measurement was performed using VICON's system. Retroactive markers and stickers were put on the airplane. JAXA's 6.5 m × 5.5 m Low-Speed Wind Tunnel was used. The airplane was mounted on the strut support with pitch-free or pitch-locked conditions. The deformations of the main wing bending, the main wing twisting, the tail boom bending, and the elevator deflection angle change were revealed quantitatively. The bending stiffness of a main wing spar that was designed as a safety factor of 2.8 at load factor of 5 was sufficient. The main wing spar was located around a center of pressure of an airfoil and it showed enough stiffness for twisting at nominal condition. The effects of the main wing bending and twisting, and the tail boom bending on the aerodynamic performance were estimated but they were in an acceptable range from the standpoint of the controllability of the aerodynamic performance using control surfaces. Even though the servo motor was located near the elevator and the linkage between the servo motor and the elevator was short, the measured elevator deflection angle was at most 4% smaller than the angle at no-wind condition. The obtained results and presented method are useful for control, flight data analysis, and design of lightweight airplanes.

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Section: Introductionmentioning

confidence: 99%

Wind Tunnel Test for Videogrammetric Deformation Measurement of UAV for Mars Airplane Balloon Experiment-1 (MABE-1)

Fujita¹,

Oyama²,

Kubo³

et al. 2019

JFCMV

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show abstract

“…Aircraft design tools such as optical measurements in wind tunnel testing, computational fluid dynamics and fluid-structure coupling techniques are developing rapidly. [1][2][3][4][5] In-flight measurement technique is necessary in order to further improve the aircraft design tool by giving the aircraft design tool the feedback on flight test data.…”

Section: Introductionmentioning

confidence: 99%

In-Flight Measurement of Wing Deformation

Kurita

Koike

Nakakita

2019

Trans. Japan Soc. Aero. S Sci.

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“…The model was fabricated with 53 upper surface 40 lower surface unsteady pressure transducers, but they were not used in control-law design or evaluation, and were not included in the simulation. A Videogrammetric Model Deformation (VMD) system 14 for tracking the motion of targets mounted on the model was employed during testing, but was not used for control-law development or evaluation and was not included in the simulation.…”

Section: Semispan Supersonic Transportmentioning

confidence: 99%

Incorporation of SemiSpan SuperSonic Transport (S4T) Aeroservoelastic Models into SAREC-ASV Simulation

Christhilf

Pototzky

Stevens

2010

AIAA Modeling and Simulation Technologies Conference

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Videogrammetric Model Deformation Measurement Technique for Wind Tunnel Applications

Cited by 33 publications

References 10 publications

Wind Tunnel Test for Videogrammetric Deformation Measurement of UAV for Mars Airplane Balloon Experiment-1 (MABE-1)

Wind Tunnel Test for Videogrammetric Deformation Measurement of UAV for Mars Airplane Balloon Experiment-1 (MABE-1)

In-Flight Measurement of Wing Deformation

Incorporation of SemiSpan SuperSonic Transport (S4T) Aeroservoelastic Models into SAREC-ASV Simulation

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