Abstract: A system and method for controlling an actuator for a control surface of an aircraft includes a processing unit configured for acquiring a set of N values of the same parameter, N being equal to 2×p or to 2×p+1, p being an integer greater than or equal to 2, and determining a voted value of the parameter by a voter (15) with N inputs. The voter with N inputs includes a module for determining two intermediate values from among the values of a subset of 2×p values of the set of N values of the parameter, this module including at least p+1 voters with 2×p?1 inputs, receiving as input distinct subsets of 2×p?1 inputs of the subset of 2×p inputs, two sub-modules for determining a maximum value and a minimum value, respectively, each receiving as input the outputs of the various voters with 2×p?1 inputs and delivering as output the two intermediate values.

Abstract: A system and method for automatically estimating a speed of an aircraft during a flight of the aircraft includes a determining module to determine at least one quantity which is representative of a force exerted on at least one control surface of the aircraft, a calculating module to calculate at least one speed of the aircraft and a transmitting module to transmit the one or more speeds of the aircraft which are calculated by the calculating module to a user device. The system makes it possible to estimate a speed of the aircraft without having to use the total pressure.

Abstract: A device for monitoring and estimating parameters relating to the flight of an aircraft includes an estimation module 4 for determining an estimation of the values of the parameters relating to the flight of the aircraft and for generating residues, a detection module for determining the statuses associated with each of said sensors C1, C2, . . . , CN and with a parameter P1 corresponding to the weight of the aircraft, a transmission module for transmitting the statuses associated with each of said sensors C1, C2, . . . , CN to a user device and, on the next iteration, to the estimation module.

Abstract: A system for assisting the maintenance of an aircraft is configured for implementing the following steps in an iterative manner determining a spectral power density of the position of a control surface over a time window; when the spectral power density corresponds to an amplitude of oscillations of the control surface upwardly crossing this predetermined threshold, storing an excess amplitude start time; and when the spectral power density corresponds to an amplitude of oscillations of the control surface downwardly crossing this predetermined threshold: determining a time interval between the excess amplitude start time and an excess amplitude end time, during which the amplitude of oscillations of the control surface has remained above the predetermined threshold; and determining an indicator representative of the energy corresponding to these oscillations during the time interval.

Abstract: A system and method for controlling an actuator for a control surface of an aircraft includes a processing unit configured for acquiring a set of N values of the same parameter, N being equal to 2×p or to 2×p+1, p being an integer greater than or equal to 2, and determining a voted value of the parameter by a voter (15) with N inputs. The voter with N inputs includes a module for determining two intermediate values from among the values of a subset of 2×p values of the set of N values of the parameter, this module including at least p+1 voters with 2×p?1 inputs, receiving as input distinct subsets of 2×p?1 inputs of the subset of 2×p inputs, two sub-modules for determining a maximum value and a minimum value, respectively, each receiving as input the outputs of the various voters with 2×p?1 inputs and delivering as output the two intermediate values.

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 device for monitoring and estimating parameters relating to the flight of an aircraft includes an estimation module 4 for determining an estimation of the values of the parameters relating to the flight of the aircraft and for generating residues, a detection module for determining the statuses associated with each of said sensors C1, C2, . . . , CN and with a parameter P1 corresponding to the weight of the aircraft, a transmission module for transmitting the statuses associated with each of said sensors C1, C2, . . . , CN to a user device and, on the next iteration, to the estimation module.

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 device for making available navigation parameter values of a vehicle is provided. The device includes components distributed in the following categories: several sensors collecting measurement data relating to at least one navigation parameter of the vehicle; several computers processing the measurement data collected by the sensors and calculating said navigation parameters; several networks linking the sensors to the computers and linking the computers to systems using said parameters. The networks transmit all the collected measurement data to the computers, which calculate a value for each navigation parameter as well as an estimated value of the associated fault, using a single common fusion algorithm.

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: Methods and devices for detecting oscillatory faults in a positional servocontrol arrangement for an aircraft control surface are provided. The detection device estimates a reference position of the control surface and, with the aid of a model in which at each iteration a residual value of the previous iteration, multiplied by a dynamic gain, is injected, detects an oscillatory fault with the aid of this reference position.

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 device for making available navigation parameter values of a vehicle is provided. The device includes components distributed in the following categories: several sensors collecting measurement data relating to at least one navigation parameter of the vehicle; several computers processing the measurement data collected by the sensors and calculating said navigation parameters; several networks linking the sensors to the computers and linking the computers to systems using said parameters. The networks transmit all the collected measurement data to the computers, which calculate a value for each navigation parameter as well as an estimated value of the associated fault, using a single common fusion algorithm.

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.