Adaptive aircraft actuator fault detection

• US 4,355,358 A
• Filed: 08/26/1980
• Issued: 10/19/1982
• Est. Priority Date: 08/26/1980
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Fowler, Donald W., Clelford, Douglas H.
• Primary Examiner(s): Smith, Jerry
• Application Number:
  US06/181,510
• Time in Patent Office: 784 Days
• Field of Search: 364/105, 364/106, 364/424, 364/434, 364/150, 364/151, 244/17.13, 244/194, 244/195, 244/196
• US Class Current: 701/3
• CPC Class Codes: G05D 1/0077 using redundant signals or controls

Abstract

The operation of an actuator (16) is monitored by comparing its position (21) with the position (31, 136) indicated by a model which integrates (45, 135) a limited amount of the difference between the position command (24) applied to the actuator and the achieved model position (31, 136), the limited amount being variable (63, 67, 124) from a nominal limit (61, 65, 124) in dependence upon limited functions (74, 90, 114, 116) of the difference (33, 109) between the actuator position and the model position, and additionally reduced (80, 94, 122) when pilot input overrides (50, 108) the position of the actuator.

Claims

1. An adaptive aircraft actuator fault detection apparatus comprising:

a mechanism for positioning a control surface of the aircraft, said mechanism including a pilot control member movable by the pilot to position said surface;

an actuator resiliently connected to said mechanism and being positionable in response to a position error signal applied thereto to determine the position of said mechanism which will have zero force applied thereto by said resilient connection;

a position detector connected to said actuator for providing a trim position signal indicative of the position of said actuator; and

signal processing means for providing a position command signal, for providing a position error signal to said actuator as the difference between said position command signal and said trim position signal, for presenting a model position signal, for providing a track error signal as the difference between said trim position signal and said model position signal, for providing a model error signal as the difference between said position command signal and said model position signal, for providing said model position signal as the integral of said model error signal to the extent that said model error signal does not exceed a limit, said limit being a nominal limit which is varied by a limited portion of said track error signal, said limit being increased in the case where said track error signal indicates that the model position is leading the actuator position and being decreased when said track error signal indicates that the model position is lagging the actuator position,and for providing a fault indication signal in response to said track error signal exceeding a threshold magnitude;

characterized by;

means associated with said signal processing means and responsive to said mechanism for providing a pilot override signal when the pilot is forcing said mechanism away from said trim position by more than a predetermined threshold amount, and said signal processing means provides said model position signal as the integral of said model error signal limited to an amount which is further reduced by a limited portion of said track error signal, in response to said pilot override signal when said track error signal indicates that the actuator position is lagging the model position.

2. An adaptive aircraft actuator fault detection apparatus according to claim 1 further characterized by said signal processing means reducing said limit to zero in response to said override signal when said track error signal indicates that the actuator position lags the model position by a predetermined amount.