It is presented and discussed the design of a custom fringe-projection system for the measurement of airplane wing surfaces, including both the tooling required to make them and the actual wing covers. Performance parameters after the first few calibration runs indicate that the specifications will enable the BLADE consortium to build the experimental natural-laminar-flow wings to the required specifications, or at least to track errors in the fabrication and assembly process. Examples from the first few measurements show that establishing overall shape deviation is difficult because it always depends on the support of the parts measured. The stitching of many sub-areas may also lead to the accumulation of small systematic errors, although this cannot be proven beyond doubt using the data thus far available. More experience will be gathered in later measurement campaigns, where all markers will be omitted and laser tracker support will be added to record all data in global so-ordinates, removing the need to align or stitch individual measurements. The data presented show that the measurement system excels at its design purpose, which is to detect and quantify waviness at the mm to sub-mm level over various length scales. By virtue of the density of measuring points, even small flaws in the surface will not escape detection, and this is an important prerequisite for understanding later under flight conditions why laminar flow exists, or does not exist, in certain areas. We anticipate being able to reduce the amount of processed data significantly in later measurement campaigns, maintaining the highest resolution only where small-scale disturbances are likely to occur.
Measurement of mould tool for laminar-flow carbon-fibre composite airplane wing cover
2014
10 Seiten, Bilder, 5 Quellen
Aufsatz (Konferenz)
Englisch
Transition Measurement of Natural Laminar Flow Wing on Supersonic Experimental Airplane NEXST-1
Online Contents | 2008
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