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| Titel |
Correction of static pressure on a research aircraft in accelerated flight using differential pressure measurements |
| VerfasserIn |
A. R. Rodi, D. C. Leon |
| Medientyp |
Artikel
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| Sprache |
Englisch
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| ISSN |
1867-1381
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| Digitales Dokument |
URL |
| Erschienen |
In: Atmospheric Measurement Techniques ; 5, no. 11 ; Nr. 5, no. 11 (2012-11-01), S.2569-2579 |
| Datensatznummer |
250003158
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| Publikation (Nr.) |
 copernicus.org/amt-5-2569-2012.pdf |
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| Zusammenfassung |
| A method is described that estimates the error in the static pressure
measurement on an aircraft from differential pressure measurements on the
hemispherical surface of a Rosemount model 858AJ air velocity probe mounted
on a boom ahead of the aircraft. The theoretical predictions for how the
pressure should vary over the surface of the hemisphere, involving an unknown
sensitivity parameter, leads to a set of equations that can be solved for the
unknowns – angle of attack, angle of sideslip, dynamic pressure and the
error in static pressure – if the sensitivity factor can be determined. The
sensitivity factor was determined on the University of Wyoming King Air
research aircraft by comparisons with the error measured with a carefully
designed sonde towed on connecting tubing behind the aircraft – a trailing
cone – and the result was shown to have a precision of about ±10 Pa over a
wide range of conditions, including various altitudes, power settings, and
gear and flap extensions. Under accelerated flight conditions, geometric
altitude data from a combined Global Navigation Satellite System (GNSS) and
inertial measurement unit (IMU) system are used to estimate acceleration
effects on the error, and the algorithm is shown to predict corrections to a
precision of better than ±20 Pa under
those conditions. Some limiting factors affecting the precision of static
pressure measurement on a research aircraft are discussed. |
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