Research on Fault Tolerant Controls within GARTEUR Hafid Smaili National Aerospace Laboratory NLR Training, Human Factors and Cockpit Operations Department Flight Mechanics, Systems and Integration Action Group FM (AG-16) CXXX-1A
Presentation Overview Introduction Recent Incidents and Accidents Aircraft accident investigation Flight 1862 FM(AG16) Benchmark FM(AG16) fault tolerant control methods Conclusions CXXX-2A
Introduction GROUP FOR AERONAUTICAL RESEARCH AND TECHNOLOGY IN EUROPE Aircraft control related incidents/accidents Pilot error Weather Systems Aircraft operating in high-risk mission operational environments Civil/Military transports External threats and crisis areas CXXX-3A
Introduction GROUP FOR AERONAUTICAL RESEARCH AND TECHNOLOGY IN EUROPE GARTEUR Action Group FM-AG16 (2004-2007) Addressing the new operational environment Improving flight safety and economics of flight Assess potential of selected FTC methods European cooperation 1 Industry partner 4 Research Institutions 6 Universities CXXX-4A
Recent Incidents and Accidents March 21, 1992, Boeing 707-321CH Freighter - Separation engines no. 3 and 4 - Successful emergency landing December 29, 1991, B747-200 Freighter - Separation engines no. 3 and 4 - Aircraft went down CXXX-5A
Recent Incidents and Accidents March 31, 1993, B747-121 Freighter - Separation engine no. 2 - Successful emergency landing CXXX-6A
Recent Incidents and Accidents October 21, 2004, B747-200 Freighter Separation engine no. 1 Successful emergency landing CXXX-7A
Recent Incidents and Accidents November 22, 2003, Airbus A300B4-203F Freighter Hit by surface-to-air missile Successful emergency landing CXXX-8A
Recent Incidents and Accidents October 4, 1992, EL AL B747-200F Freighter, Flight 1862 Multiple right wing engine separation Aircraft went down into the Amsterdam Bijlmermeer, 13 km east of Amsterdam Schiphol Airport CXXX-9A
Recent Incidents and Accidents Flight 1862 failure configuration Control Surface Lost 50% Hinge Moment Loss / Half Trim Rate CXXX-10A
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Aircraft accident investigation Flight 1862 Flight reconstruction Setup Based on Inverse Simulation Principle CXXX-12A
Aircraft accident investigation Flight 1862 EL AL Flight 1862 Leg 2 / Flaps up EL AL Flight 1862 Control Wheel Position (deg) 20 10 0-10 -20-30 -40-50 -60-70 -80 FDRS DFDR Control Wheel Position (deg) 20 10 0-10 -20-30 -40-50 -60-70 -80 400 450 500 550 600 650 Time (s) 400 450 500 Time Reconstructed Control Wheel Deflection (Without Aerodynamic Estimates) Reconstructed Control Wheel Deflection (Including Aerodynamic Estimates) CXXX-13A
Aircraft accident investigation Flight 1862 EL AL Flight 1862 Leg 2 / Flaps up EL AL Flight 1862 40 30 20 FDRS DFDR 40 30 20 Roll Angle (deg) 10 0-10 -20 Roll Angle (deg) 10 0-10 -20-30 -40-30 -40 400 450 500 550 600 650 Time (s) Reconstructed Roll Angle (Without Aerodynamic Estimates) 400 450 500 Tim Reconstructed Roll Angle (Including Aerodynamic Estimates) CXXX-14A
FM(AG16) Benchmark Detailed simulation model of B747-200 developed for the Bijlmermeer investigation Validated against accident flight data Adapted/extended for the AG-16 benchmark fault generator scenario generator assessment criteria evaluation autoflight system separate control surfaces CXXX-15A
FM(AG16) Benchmark Failure cases Stuck or erroneous elevator Stuck or erroneous aileron Elevator/stabiliser runaway Stuck, erroneous or rudder runaway Loss of vertical tail surface Engine separation + resulting structural damage CXXX-16A
FM(AG16) Benchmark normal flight failure initial recovery parameter identification straight flight right-hand turn final approach glideslope intercept localizer intercept The overall goal is to prove safe landing at a nearby airfield CXXX-17A
FM(AG16) Benchmark failures Benchmark generator Modern Controller 30 controls FBW Aircraft Sensors Simulation environment for modern controller implementation CXXX-18A
FM(AG16) fault tolerant control methods Robust Same controller deals with range of conditions Adaptive Controller structure fixed Parameters respond to track changes in aircraft Fault-tolerant / reconfigurable Fault Detection and Isolation (FDI) Actuator/sensor status feedback Controller re-designed on the fly CXXX-19A
FM(AG16) fault tolerant control methods Benchmark challenges the AG16 partners Hull / Brunel: Analytic redundancy Lille: Analytic redundancy, Control re-allocation Leicester: Sliding modes Aalborg: Interacting Multiple models Cambridge: Model Predictive Control (MPC) Delft / NLR: MPC + Nonlinear Dynamic Inversion QinetiQ: Nonlinear Dynamic Inversion DLR: Least-order filter design CIRA: Trim analysis of nonlinear model (previous presentation) CXXX-20A
Conclusions GROUP FOR AERONAUTICAL RESEARCH AND TECHNOLOGY IN EUROPE Airplane operations shift into new operational environment Civil/military operations in potentially high-risk mission environments (external threats / crisis areas) GARTEUR FM(AG16) addresses new operational environment Providing challenging research environment to assess potential technological solutions CXXX-21A
Meanwhile at a bus stop in Toulouse. CXXX-22A