Method and device for detecting a failure on an aircraft
AssigneesAirbus Operations GmbH, Institut Polytechnique De Bordeaux, Centre National De La Recherche Scientifique, Universite De Bordequx
InventorsAnca Gheorghe, Philippe Goupil, Rémy Dayre, Ali Zolghadri, Jérôme Cieslak, Denis Efimov
Life of this patent
Estimating the term…
Abstract
The detecting means (1) comprise measuring means (2) adapted to measure and provide at least one raw data corresponding to an aircraft parameter, computing means (3) adapted to estimate at least one derivative of said raw data, and detecting means (4) adapted to detect a failure with the aid of said derivative, said computing means (3) being adapted to estimate said derivative by differentiation.
Claims12
A method for detecting a fault on an aircraft, comprising the following successive steps implemented in an automated and repeated manner:
- a) providing a control surface on the aircraft, wherein the control surface is adapted to be moved to control the aircraft;
- b) monitoring a movement parameter indicative of the movement of the control surface on the aircraft by a single sensor;
- c) outputting by the single sensor at least one noisy datum indicating the movement parameter;
- d) receiving the at least one noisy datum output by the sensor, wherein the derivative of the at least one noisy datum is established by a sliding mode differentiator;
- e) estimating a derivative of said at least one noisy datum by differentiation, on the basis of said at least one noisy datum;
- f) detecting a fault on the basis of at least the estimated derivative, and
- g) declaring the fault as a failure of the control surface in conjunction with monitoring performance of the aircraft.
An aircraft comprising:
- a control surface configured to move in response to a pilot command;
- a single control surface movement sensor configured to monitor movements of the control surface and transmit at least one noisy datum indicative of movement of the control surface;
- device for detecting a fault of the control surface on an aircraft in connection with monitoring performance of the aircraft, wherein the device comprises:
- a computing unit adapted to estimate at least one derivative of said at least one noisy datum, wherein, the derivative of said at least one noisy datum is estimated by a sliding mode differentiator;
- and
- a detector adapted to detect the fault on the basis of said derivative and declare the fault to be a failure of the control surface.
Dependencies are inferred from the claim text.