Detection of actuator faults in flight control systems

A method for the multiple fault diagnosis of aircraft traditional aerodynamic control surfaces described by a nonlinear model is proposed in the form of an algorithm. A geometric approach to the nonlinear fault detection and isolation problem is investigated for actuator fault detection. The approach is based on the geometric decomposition of aircraft dynamics into tangential and transverse dynamics. Its application to reconstructed flight fault dynamics enables fault detection and distinguishes which one is occurring. To efficiently identify safety issues, critical contingencies leading the system to a failure state can be evaluated using effective algorithms within each functional area of the whole system. Results of the proposed approaches indicate not only the effective identification of faults in civil transport aircraft but also improvements in establishing an acceptable level of safety performance, even when the number of faults is not known a priori.

[1]  Paul M. Frank,et al.  Fault diagnosis in dynamic systems using analytical and knowledge-based redundancy: A survey and some new results , 1990, Autom..

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

[3]  Rolf Isermann,et al.  Process fault detection based on modeling and estimation methods - A survey , 1984, Autom..

[4]  Janos Gertler,et al.  Robust FDI systems and H/sub /spl infin//-optimization-disturbances and tall fault case , 1993, Proceedings of 32nd IEEE Conference on Decision and Control.

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

[6]  M. Massoumnia.  A geometric approach to the synthesis of failure detection filters , 1986 .

[7]  M. Najim.  0 - Modélisation et identification en traitement du signal , 1987 .

[8]  Youmin Zhang,et al.  Integrated active fault-tolerant control using IMM approach , 2001 .

[9]  A. Isidori.  Nonlinear Control Systems , 1985 .

[10]  Alan S. Willsky,et al.  A survey of design methods for failure detection in dynamic systems , 1976, Autom..

[11]  Salim Chaib,et al.  Projector-based switching signal reconstruction and observer for switched systems , 2007, 2007 46th IEEE Conference on Decision and Control.

[12]  Petros A. Ioannou,et al.  Accommodation of failures in the F-16 aircraft using adaptive control , 1991, IEEE Control Systems.

[13]  Hassan Hammouri,et al.  Observer-based approach to fault detection and isolation for nonlinear systems , 1999, IEEE Trans. Autom. Control..

[14]  S. Glavaski,et al.  Reconfigurable control for active management of aircraft system failures , 2001, Proceedings of the 2001 American Control Conference. (Cat. No.01CH37148).

[15]  Alberto Isidori,et al.  A geometric approach to nonlinear fault detection and isolation , 2000, IEEE Trans. Autom. Control..

[16]  Petros G. Voulgaris,et al.  DIRECT ADAPTIVE RECONFIGURABLE FLIGHT CONTROL FOR A TAILLESS ADVANCED FIGHTER AIRCRAFT , 1999 .

[17]  Ravi N. Banavar,et al.  A loop transfer recovery approach to the control of an electro-hydraulic actuator , 1998 .

[18]  Rolf Isermann,et al.  Process Fault Detection Based on Modeling and Estimation Methods , 1982 .

[19]  Brad Seanor,et al.  A fault tolerant flight control system for sensor and actuator failures using neural networks , 2000 .

[20]  Jie Chen,et al.  Robust Model-Based Fault Diagnosis for Dynamic Systems , 1998, The International Series on Asian Studies in Computer and Information Science.

[21]  Jakob Stoustrup,et al.  Fault detection for nonlinear systems - a standard problem approach , 1998, Proceedings of the 37th IEEE Conference on Decision and Control (Cat. No.98CH36171).

[22]  Andres Marcos,et al.  Linear Parameter Varying Modeling of the Boeing 747-100/200 Longitudinal Motion , 2001 .

[23]  Yasuji Shibahata,et al.  Two-degree-of-freedom hydraulic pressure controller design for direct yaw moment control system , 1999 .

[24]  David G. Ward,et al.  IMPLEMENTATION AND FLIGHT TEST ASSESSMENT OF AN ADAPTIVE, RECONFIGURABLE FLIGHT CONTROL SYSTEM , 1997 .

[25]  R. K. Mehra,et al.  An adaptive scheme for compensation of loss of effectiveness of flight control effectors , 2001, Proceedings of the 40th IEEE Conference on Decision and Control (Cat. No.01CH37228).