AMT-200S Motor Glider Parameter and Performance Estimation
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NASA/TM—2011–215974 AMT-200S Motor Glider Parameter and Performance Estimation Brian R. Taylor Dryden Flight Research Center, Edwards, California Click here: Press F1 key (Windows) or Help key (Mac) for help July 2011 This page is required and contains approved text that cannot be changed. NASA STI Program ... in Profile Since its founding, NASA has been dedicated • CONFERENCE PUBLICATION. to the advancement of aeronautics and space Collected papers from scientific and science. The NASA scientific and technical technical conferences, symposia, information (STI) program plays a key part in seminars, or other meetings sponsored helping NASA maintain this important role. or co-sponsored by NASA. The NASA STI program operates under the • SPECIAL PUBLICATION. Scientific, auspices of the Agency Chief Information technical, or historical information from Officer. It collects, organizes, provides for NASA programs, projects, and missions, archiving, and disseminates NASA’s STI. 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NOTICE Use of trade names or names of manufacturers in this document does not constitute an official endorsement of such products or manufacturers, either expressed or implied, by the National Aeronautics and Space Administration. Click here: Press F1 key (Windows) or Help key (Mac) for help Available from: NASA Center for AeroSpace Information 7115 Standard Drive Hanover, MD 21076-1320 443 -757-5802 Click here: Press F1 key (Windows) or Help key (Mac) for help Abstract Parameter and performance estimation of an instrumented motor glider was conducted at the National Aeronautics and Space Administration Dryden Flight Research Center in order to provide the necessary information to create a simulation of the aircraft. An output-error technique was employed to generate estimates from doublet maneuvers, and performance estimates were compared with results from a well-known flight-test evaluation of the aircraft in order to provide a complete set of data. Aircraft specifications are given along with information concerning instrumentation, flight-test maneuvers flown, and the output-error technique. Discussion of Cramér-Rao bounds based on both white noise and colored noise assumptions is given. Results include aerodynamic parameter and performance estimates for a range of angles of attack. Nomenclature an normal acceleration, g an normal acceleration bias, g b ax axial acceleration, g ax axial acceleration bias, g b ay lateral acceleration, g ay lateral acceleration bias, g b b reference span, ft C.G. center of gravity C total axial force coefficient A C axial force coefficient due to pitch rate Aq CA0 trim axial force coefficient C axial force coefficient due to angle of attack Aα C 2 axial force coefficient due to the square of the angle of attack Aα C axial force coefficient due to elevator deflection Aδe C total coefficient of drag D C total coefficient of lift L C trim lift coefficient L0 C lift coefficient due to angle of attack (lift curve slope) Lα C 2 lift coefficient due to the square of the angle of attack Lα C total rolling moment coefficient l C rolling moment coefficient due to roll rate lp C rolling moment coefficient due to yaw rate lr C trim rolling moment coefficient l0 C rolling moment coefficient due to angle of sideslip lβ C rolling moment coefficient due to aileron deflection lδa C rolling moment coefficient due to rudder deflection lδr C total pitching moment coefficient m C pitching moment coefficient due to pitch rate mq C trim pitching moment coefficient m0 C pitching moment coefficient due to angle of attack mα C pitching moment coefficient due to elevator deflection mδe CN total normal force coefficient C normal force coefficient due to pitch rate Nq C trim normal force coefficient N0 C normal force coefficient due to angle of attack Nα C 2 normal force coefficient due to the square of the angle of attack Nα C normal force coefficient due to elevator deflection Nδe C total yawing moment coefficient n C yawing moment coefficient due to roll rate np C yawing moment coefficient due to yaw rate nr C trim yawing moment coefficient n0 C yawing moment coefficient due to angle of sideslip nβ C yawing moment coefficient due to aileron deflection nδa C yawing moment coefficient due to rudder deflection nδr CY total lateral force coefficient C lateral force coefficient due to rudder deflection Ydr C lateral force coefficient due to roll rate Yp C lateral force coefficient due to yaw rate Yr C trim lateral force coefficient Y0 C lateral force coefficient due to angle of sideslip Yβ C lateral force coefficient due to aileron deflection Yδa c reference chord, ft D axial displacement between main gear and tail wheel, ft FAA Federal Aviation Administration F measured force at left main landing gear, lb LM F measured force at right main landing gear, lb RM F measured force at tail, lb T g acceleration due to gravity, ft/s2 2 H vertical displacement between scales, ft IMU inertial measurement unit I roll moment of inertia, slug-ft2 x I pitch moment of inertia, slug-ft2 y I yaw moment of inertia, slug-ft2 z I roll-yaw moment of inertia, slug-ft2 xz KCAS knots calibrated airspeed k upwash coefficient α k sidewash coefficient β MSL mean sea level m mass, slug NASA National Aeronautics and Space Administration p roll rate, deg/s p measured roll rate, deg/s Z p roll rate bias, deg/s b p roll rate time derivative, deg/s/s q pitch rate, deg/s q measured pitch rate, deg/s Z q pitch rate bias, deg/s b 2 q dynamic pressure, lb/ft q pitch rate time derivative, deg/s/s r yaw rate, deg/s r measured yaw rate, deg/s Z r yaw rate bias, deg/s b r yaw rate time derivative, deg/s/s S wing area, ft2 TPS Test Pilot School USAF United States Air Force v velocity, ft/s W total aircraft weight, lb X longitudinal displacement of the normal accelerometer from the aircraft center of gravity, an ft X longitudinal displacement of the axial accelerometer from the aircraft center of gravity, ft ax X longitudinal displacement of the lateral accelerometer from the aircraft center of gravity, ay ft X longitudinal position, body coordinate system, ft b X longitudinal displacement of the angle of attack vane from the aircraft center of gravity, ft α X longitudinal displacement of the angle of sideslip vane from the aircraft center of gravity, β ft 3 Y lateral displacement of the normal accelerometer from the aircraft center of gravity, ft an Y lateral displacement of the axial accelerometer from the aircraft center of gravity, ft ax Y lateral displacement of the lateral accelerometer from the aircraft center of gravity, ft ay Y lateral position, body coordinate system, ft b Y lateral displacement of the angle of attack vane from the aircraft center of gravity, ft α Z vertical displacement of the normal accelerometer from the aircraft center of gravity, ft an Z vertical displacement of the axial accelerometer from the aircraft center of gravity, ft ax Z vertical displacement of the lateral accelerometer from the aircraft center of gravity, ft ay Z vertical position, body coordinate system, ft b Z vertical displacement of the angle of sideslip vane from the aircraft center of gravity, ft β α angle of attack, deg α measured angle of attack, deg Z α angle of attack bias, deg b α angle of attack time derivative, deg/s β angle of sideslip, deg β measured angle of sideslip, deg Z β angle of sideslip bias, deg b angle of sideslip time derivative, deg/s β δe elevator deflection, deg Θ pitch angle, deg θ aircraft inclination angle, deg Φ bank angle, deg 1.