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.

Abstract: A detection device comprising a first data processing unit configured to determine a first trend of the control surface control order as a function of time, the first trend being defined according to a reference parameter, a second data processing unit configured to determine at least one second trend of the control surface position value as a function of time, the second trend being also defined according to the reference parameter, and a monitoring unit configured to compare the first and second trends in order to verify the existence of a correlation between these first and second trends so as to detect an oscillatory failure as soon as a loss of correlation between the first and second trends appears, if necessary.

Abstract: A device including a first data generating unit for determining at least one aerodynamic hinge moment of at least one control surface of the aircraft, a second data generating unit for determining a plurality of data and at least one external static pressure and a model of hinge moment coefficient, a computation unit for computing with the aid of these data at least one speed of the aircraft, namely a Mach number and/or a conventional speed, and a data transmission unit for providing this speed to a user system.

Abstract: A detection device comprising a first data processing unit configured to determine a first trend of the control surface control order as a function of time, the first trend being defined according to a reference parameter, a second data processing unit configured to determine at least one second trend of the control surface position value as a function of time, the second trend being also defined according to the reference parameter, and a monitoring unit configured to compare the first and second trends in order to verify the existence of a correlation between these first and second trends so as to detect an oscillatory failure as soon as a loss of correlation between the first and second trends appears, if necessary.

Abstract: A device including a first data generating unit for determining at least one aerodynamic hinge moment of at least one control surface of the aircraft, a second data generating unit for determining a plurality of data and at least one external static pressure and a model of hinge moment coefficient, a computation unit for computing with the aid of these data at least one speed of the aircraft, namely a Mach number and/or a conventional speed, and a data transmission unit for providing this speed to a user system.

Abstract: A system for detecting jamming and/or uncontrolled movement of an aircraft control surface includes first means for estimating the value of at least one parameter of an equation simulating the feedback loop dynamic of the control surface, according to a recursive autoregressive method with exogenous variable of RARX type in a recursive least squares way, and second means for detecting jamming and/or uncontrolled movement of the control surface, according to the estimated parameter value by the application of a decision test in the parametric space.

Abstract: Embodiments of the disclosure include methods and devices in which a flight parameter vector for an aircraft is automatically estimated and then compared to a threshold to determine whether the flight parameter vector is accurate. The detection device estimates a coefficient vector in an observation window, calculates an estimated flight parameter value, and minimizes an error associated with the observation window when calculating the estimated flight parameter value of the flight parameter vector. Comparisons may be performed by a failure detector or a flight control computer to determine failures impacting the flight parameter vector.

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.

Abstract: A detection device determines whether an uncontrolled movement of a control surface of an aircraft is occurring. The device includes means for calculating the difference between a theoretical command and an actual command in order to form a residual value, and means for detecting an uncontrolled movement of the control surface, if a comparison value depending on this residual value is greater than a threshold value If the comparison value is greater than the threshold value during a confirmation time, then the uncontrolled movement of the control surface of the aircraft is confirmed.

Abstract: A system for detecting jamming and/or uncontrolled movement of an aircraft control surface includes first means for estimating the value of at least one parameter of an equation simulating the feedback loop dynamic of the control surface, according to a recursive autoregressive method with exogenous variable of RARX type in a recursive least squares way, and second means for detecting jamming and/or uncontrolled movement of the control surface, according to the estimated parameter value by the application of a decision test in the parametric space.

Abstract: The detection device includes, but is not limited to a device that is configured to determine a control error corresponding to the difference between a first control instruction and a control surface position, a second device that is configured to calculate the difference between this control error and a second control instruction in such a way as to form a comparison signal, and a third device that is configured to detect a jamming of the control surface if this comparison signal is greater than a threshold value.

Abstract: The detection device includes, but is not limited to a device that is configured to determine a control error corresponding to the difference between a first control instruction and a control surface position, a second device that is configured to calculate the difference between this control error and a second control instruction in such a way as to form a comparison signal, and a third device that is configured to detect a jamming of the control surface if this comparison signal is greater than a threshold value.

Abstract: Automatic estimation process and device for a flight parameter vector in an aircraft, as well as detection methods and assemblies for a failure affecting such a vector. The detection device (1) comprises means (5) for estimating, on an observation window, a coefficient vector allowing to determine a linear relationship between the searched flight parameter vector and explanatory values, by implementing a PLS regression, and means (5) to use such a coefficient vector so as to calculate, thru a linear modeling, an estimated value of said flight parameter vector.

Abstract: Method and device for detecting an uncontrolled movement of an aircraft control surface. The detection device (1) comprises means (29) for calculating the difference between a theoretical command and an actual command in order to form a residual value, and means (40) for detecting an uncontrolled movement of the control surface, if a comparison value depending on this residual value is greater than a threshold value (?).

Abstract: A device and a method for automatically generating a control order of an aircraft control surface. The device can include means for automatically calculating and transmitting, in the case of a suspected deficiency of a control surface control order, a limited auxiliary order, during a confirmation time of the deficiency.

Abstract: This invention relates to a system for processing redundant signals, an associated method, as well as an aircraft comprising such a system, from a viewpoint of monitoring and passivation of erratic or oscillating failures affecting the sources of these redundant signals. The system comprises a module for calculation of a current useful signal from redundant signals; a monitoring/passivation module, able to detect an erroneous signal and to exclude the said erroneous signal from the calculation according to a criterion; and a means for toggling, as soon as an erroneous signal is detected, to a freeze mode freezing the output useful signal, and for returning, as soon as an erroneous signal no longer is detected, to a transmission mode where the current useful signal is transmitted as output useful signal.

Abstract: A device and a method for automatically generating a control order of an aircraft control surface The device (1) comprises means (9) for automatically calculating and transmitting, in the case of a suspected deficiency of a control surface control order, a limited auxiliary order, during a confirmation time of the deficiency.