By Fritz Boden, Nicholas Lawson, Henk W. Jentink, Jürgen Kompenhans
The booklet provides a synopsis of the most effects accomplished throughout the three 12 months EU-project "Advanced Inflight dimension options (AIM)" which utilized complex photo established dimension recommendations to business flight checking out. The ebook is meant to be not just an outline at the target actions but additionally a advisor at the software of complicated optical dimension thoughts for destiny flight checking out. additionally it's a necessary advisor for engineers within the box of experimental equipment and flight trying out who face the problem of a destiny requirement for the advance of hugely actual non-intrusive in-flight dimension options.
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Additional info for Advanced In-Flight Measurement Techniques
Like surface finish, quality of the dot pattern, reflectance, camera noise and uncertainties in the correlation algorithm, which will appear during a real experiment. 8 mm in Y direction (horizontally in spanwise direction). The accuracies in dZ and dX direction are better than the one in Y direction because they are more in line with the camera sensor coordinates, while the distance in Y direction equals the depth of the camera system which is related to the angle between the cameras. 36 F. Boden et al.
Measuring fuel consumption contributed to the calculation of the aircraft weight reduction during the complete flight. This accurate aircraft weight was required for the determination of the normal load. 1 IPCT Static Results As the reference condition a straight level flight condition (load factor 1) was used, selected from the beginning of the flight. Vertical displacements at 0 and 2 g over 24 H. P. J. Veerman et al. 2 g vertical displacement on main wing [mm] -100 -50 -200 -52 -300 -54 -400 -56 -500 -58 -600 -60 -700 -62 -800 -64 -900 -66 -1,000 y (geometrical frame) [mm] y (geometrical frame) [mm] 0 g vertical displacement on main wing [mm] -68 -200 -100 0 -100 70 -200 68 -300 66 -400 64 -500 62 -600 60 -700 58 -800 56 -900 54 -1,000 52 -200 -100 0 100 200 300 400 500 100 200 300 400 500 x (geometrical frame) [mm] x (geometrical frame) [mm] Fig.
For this purpose, a thin generic half wing model was used. Thus, it was possible to assume that the acceleration and deformation is identical on the upper and the lower wing surface. Based on this assumption the dot pattern was attached on the upper surface of the wing and the accelerometers were mounted at the lower wing surface. Hence it was possible to measure with both methods in the same place at the same time. For a first estimate of the excitation to be expected, the deformation was measured with a laser vibrometer too.
Advanced In-Flight Measurement Techniques by Fritz Boden, Nicholas Lawson, Henk W. Jentink, Jürgen Kompenhans