Fault-Tolerant Control on a UH-60 Black Hawk helicopter using horizontal stabilator

The present study proposes an augmentation to the existing control mixing on the UH-60 Black Hawk to utilize the horizontal stabilator as a control effector in the feedback control to compensate for locked-in-place failure in the main-rotor swashplate actuators. Stabilator use has previously been shown to work in an adaptive sense, where the control mixing is remapped in flight once failure is detected. Now it is shown to perform well when the defined mixing utilizes the stabilator even on the undamaged aircraft, removing the need to detect and identify specific failures on the aircraft. Post-failure, the aircraft retains level 1 handling qualities ratings in pitch bandwidth and disturbance rejection. For forward actuator failure, the aircraft departs level 1 in the vertical rate response and pitch stability margin. There is a general improvement in handling qualities ratings as stabilator authority is increased. The aircraft is simulated flying a trajectory to a recoverable state post-failure, where the descent rate and forward speed are appropriate for a rolling landing. Stabilator hardover is also considered; the aircraft is shown to compensate for a stabilator hardover at a moderate flight speed, retaining level 1 handling qualities with only minor degradation relative to the undamaged aircraft except for failure at 80 knots showing level 3 stability margins.

[1]  Mark G. Ballin.  Validation of a real-time engineering simulation of the UH-60A helicopter , 1987 .

[2]  Farhan Gandhi,et al.  Using Redundant Effectors to Trim a Compound Helicopter with Damaged Main Rotor Controls , 2017 .

[3]  Mark B. Tischler,et al.  Aircraft and Rotorcraft System Identification: Engineering Methods with Flight-Test Examples , 2006 .

[4]  James F. Stewart,et al.  Flight-testing of the self-repairing flight control system using the F-15 highly integrated digital electronic control flight research facility , 1990 .

[5]  Jennie Si,et al.  Helicopter Flight-Control Reconfiguration for Main Rotor Actuator Failures , 2003 .

[6]  Ronald A. Hess.  A Framework for Robust Rotorcraft Flight Control Design , 2011 .

[7]  J. Gordon Leishman,et al.  Comparison of Advanced RANS Modeling with Dual-Plane PIV Measurements for a Hovering Rotor , 2018 .

[8]  Eric K. Shinseki,et al.  Operator's Manual for UH-60A Helicopter, UH-60L Helicopter, EH-60A Helicopter , 1996 .

[9]  Frank L. Lewis,et al.  Aircraft control and simulation: Dynamics, controls design, and autonomous systems: Third edition , 2015 .

[10]  Gareth D. Padfield,et al.  Helicopter Flight Dynamics , 2000 .

[11]  Marc Bodson,et al.  Multivariable adaptive algorithms for reconfigurable flight control , 1997, IEEE Trans. Control. Syst. Technol..

[12]  P. R. Chandler,et al.  Self-repairing flight control system program overview , 1988, Proceedings of the IEEE 1988 National Aerospace and Electronics Conference.

[13]  Michael W. Heiges.  Reconfigurable Controls for Rotorcraft — A Feasibility Study , 1997 .

[14]  Kevin A. Wise,et al.  Flight Testing of Reconfigurable Control Law on the X-36 Tailless Aircraft , 2001 .

[15]  David A. Peters,et al.  Technical Note: Dynamic Inflow for Practical Applications , 1988 .

[16]  M. McKay,et al.  Horizontal Stabilator Utilization for Post Swashplate Failure Operation on a UH-60 Black Hawk Helicopter , 2020 .

[17]  Farhan Gandhi,et al.  Flight simulation and control of a helicopter undergoing rotor span morphing , 2017 .

[18]  F J Bailey.  A simplified theoretical method of determining the characteristics of a lifting rotor in forward flight , 1941 .

[19]  David A. Peters,et al.  Dynamic inflow for practical applications , 1988 .

[20]  J. J. Howlett.  UH-60A Black Hawk engineering simulation program. Volume 1: Mathematical model , 1981 .