Method and system for in-flight fault monitoring of flight control actuators
First Claim
1. A method for monitoring in-flight fault characteristics of aircraft flight control actuators, the method comprising:
- commanding a first actuator via a first command signal;
commanding a second actuator via a second command signal contemporaneously with the first command signal, wherein the first command signal and the second command signal are configured such that in combination they are expected to produce substantially no motion of the aircraft; and
monitoring the aircraft for unexpected motion.
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Accused Products
Abstract
A method and system for detecting in-flight fault characteristics of flight control actuators is provided. Commands are sequentially sent to sets of actuators during flight in a manner that is expected to produce little or no net aircraft motion. The detection of motion indicates the possibility of a faulty actuator. If additional tests confirm the failure, the actuator is isolated and other actuators are compensated to adjust for the failed actuator, permitting continuation of safe and controllable fight by the flight crew and control for a safe landing. This isolation of the suspect failed actuator serves to prevent a possible upset of the aircraft control should the suspect actuator completely fail to a large offset condition, due to continued use during flight, a situation that may cause loss of control of the aircraft.
100 Citations
20 Claims
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1. A method for monitoring in-flight fault characteristics of aircraft flight control actuators, the method comprising:
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commanding a first actuator via a first command signal;
commanding a second actuator via a second command signal contemporaneously with the first command signal, wherein the first command signal and the second command signal are configured such that in combination they are expected to produce substantially no motion of the aircraft; and
monitoring the aircraft for unexpected motion. - View Dependent Claims (2, 3, 4, 5, 6, 7)
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8. A system for in-flight fault detection of flight control actuators, the system comprising:
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a plurality of aircraft flight control surfaces;
at least one actuator in communication with each of the aircraft flight control surfaces;
a computer processor in communication with the actuators; and
a memory associated with the computer processor and containing stored programming instructions that, when operated by the computer processor, cause the processor to;
command a first actuator via a first command signal;
command a second actuator via a second command signal contemporaneously with the first command signal, wherein the first command signal and the second command signal are configured such that in combination they are expected to produce substantially no motion of the aircraft; and
monitor the aircraft for unexpected motion. - View Dependent Claims (9, 10, 11, 12, 13, 14)
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15. A system for in-flight fault detection of flight control actuators, the system comprising:
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a plurality aircraft flight control surfaces;
at least one actuator in communication with each of the aircraft flight control surfaces;
a means for commanding a first actuator via a first command signal and commanding a second actuator via a second command signal contemporaneously with the first command signal, wherein the first command signal and the second command signal are configured such that in combination they are expected to produce substantially no motion of the aircraft; and
a means for monitoring the aircraft for unexpected motion. - View Dependent Claims (16, 17, 18, 19, 20)
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Specification