Reliable Dual-redundant Sensor Failure Detection and Identification for the NASA F-8 DFBW AircraftNational Aeronautics and Space Administration, Scientific and Technical Information Office, 1978 - Airplanes - 216 pages |
Contents
ANALYTIC REDUNDANCY SPRTs | 15 |
APPLICATION TO FLIGHT TEST DATA | 53 |
5 | 61 |
3 other sections not shown
Common terms and phrases
acceleration bias accelerometer outputs aircraft alpha vane altimeter altitude kinematics analytic redundancy tests BFM Bias bias failure calculations computed crosses the failure direct redundancy trigger Directional gyro DR SPRT error sources ETL's Euler angle failed instrument failure detection failure identification failure threshold FDI algorithm Figure flight fly-by-wire form of analytic gyro biases high turbulence identified as failed indicates initialization error instrument type lateral accelerometer longitudinal accelerometers loop logic m/sec² Mach meter magnitude measurement noise Non-horizontal Spin normal accelerometer outer loop parameters pitch rate gyro provisionally failed rad/sec ramp residuals for instrument RK QSPRT RK residuals roll rate gyro rotational kinematics sample seconds Section Segment 4A sensor simulation spin axis SPRT for instrument SPRT output TD QSPRT telemetry translational dynamics translational kinematics SPRT's transonic Trigger Performance Turn Error Compensation unfailed variance vector vertical gyro wind shear worst-case yaw rate gyro zero