The effects of pressure sensor acoustics on airdata derived from a high-angle-of-attack flush airdata sensing (HI-FADS) systemThe accuracy of a prototype nonintrusive airdata system derived for high-angle-of-attack measurements was demonstrated for quasi-steady maneuvers as great as 55 degrees during phase one of the F-18 high alpha research vehicle flight test program. This system consists of a matrix of nine pressure ports arranged in annular rings on the aircraft nose, and estimates the complete airdata set utilizing flow modeling and nonlinear regression. Particular attention is paid to the effects of acoustical distortions within the individual pressure sensors of the HI-FADS pressure matrix. A dynamic model to quantify these effects which describes acoustical distortion is developed and solved in closed form for frequency response.
Document ID
19910034781
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Whitmore, Stephen R. (NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Moes, Timothy R. (NASA Flight Research Center Edwards, CA, United States)