Measuring and testing – Wind tunnel: aerodynamic wing and propeller study
Reexamination Certificate
2007-08-14
2007-08-14
Lefkowitz, Edward (Department: 2855)
Measuring and testing
Wind tunnel: aerodynamic wing and propeller study
Reexamination Certificate
active
11262678
ABSTRACT:
A method for designing aircraft including providing a model of the aircraft and a plurality of sensors mounted on the model. The method further includes positioning the aircraft model in a fluid tunnel at an initial attitude and measuring an initial orientation of the aircraft model while the aircraft model is at the initial attitude using a first tilt sensor of the sensors to create initial orientation information. The method also includes passing fluid over the aircraft model using the fluid tunnel and actively moving the aircraft model from the initial attitude to a subsequent attitude. In addition, the method includes measuring a subsequent orientation of the aircraft model while the aircraft model is at the subsequent attitude using a first orientation sensor of the sensors to create subsequent orientation information.
REFERENCES:
patent: 4862739 (1989-09-01), Dobbs
patent: 4920791 (1990-05-01), Griffin
patent: 5020364 (1991-06-01), Manitt et al.
patent: 5345818 (1994-09-01), Magill et al.
patent: 6571618 (2003-06-01), Demay et al.
patent: 63235844 (1988-09-01), None
patent: 01299434 (1989-12-01), None
patent: 05187961 (1993-07-01), None
Crites, R. C., “Development of a Simple Optical Pitch Sensor,” AIAA 86-0770, 1986.
Crawford, B. L. et al., “Improved Correction System for Vibration Sensitive Inertial Angle of Attack Measurement Devices,” AIAA 2000-0415, 2000.
Fuykschot, P. H., “Vibration Compensation of Gravity Sensing Inclinometers in Windtunnel Models,” NLR Technical Publication TP 96003 L, 2003.
Lawrence, A.,Modern Inertial Technology, Ch. 9 “The Dynamically Tuned Gyroscope,” 2nded., Springer-Verlag, New York, 1992.
Liu, T, et al., “Photogrammetry Applied to Wind-Tunnel Testing,”AIAA Journal, vol. 38, No. 6, 2000, pp. 964-971.
Rueger, M.L. et al., “Transonic Wind Tunnel Boundary Interference Correction,”AGARD Conference Proceedings 535, Wall Interference, Support Interference, and Flow Field Measurements, AGARD-CP-535, Advisory Group for Aerospace Research and Development, 1994.
Ruyten, W., “Model Attitude Measurement with an Eight-Camera Pressure-Sensitive Paint System,” AIAA 2000-0831, 2000.
Tcheng, P., et al., “Effects of Yaw and Pitch Motion on Model Attitude Measurements,” NASA TM-4641, 1995.
Jenkins Jermaine
Lee & Hayes PLLC
Lefkowitz Edward
The Boeing Company
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