(19)
(11)EP 2 077 475 A3

(12)EUROPEAN PATENT APPLICATION

(88)Date of publication A3:
07.03.2012 Bulletin 2012/10

(43)Date of publication A2:
08.07.2009 Bulletin 2009/28

(21)Application number: 08075971.5

(22)Date of filing:  30.12.2008
(51)International Patent Classification (IPC): 
G05B 23/02(2006.01)
(84)Designated Contracting States:
AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR
Designated Extension States:
AL BA MK RS

(30)Priority: 03.01.2008 US 969150

(71)Applicant: THE BOEING COMPANY
Chicago, IL 60606-2016 (US)

(72)Inventors:
  • Mossman, David C.
    Gilbert, Arizona 85234 (US)
  • Enns, Russell J.
    Chandler, Arizona 85224 (US)
  • Dahman, Jonathan B.
    Gilbert, Arizona 85296 (US)

(74)Representative: Land, Addick Adrianus Gosling et al
Arnold & Siedsma Sweelinckplein 1
2517 GK Den Haag
2517 GK Den Haag (NL)

  


(54)Control system actuation fault monitoring


(57) Methods and apparatus for monitoring and detecting failures in the actuation of a control system, such as a flight control system for an aircraft, include defining a nominal model of the control system in terms of the state variables of the control system, defining a model of an asymmetric "actuation monitoring envelope" that dynamically bounds a range that measured state variables of the system are allowed to take during operation of the system as a function of the nominal system state model, monitoring a signal corresponding to a state variable of the system during operation thereof, and detecting a failure in the actuation of the control system when the monitored signal exceeds the bounds of the monitoring envelope.







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