Abstract: Method and system for merging measurements of flight parameters of an aircraft. The system is for merging measurements of flight parameters of an aircraft, linked to one another by at least one equation, and includes at least one acquisition module for acquiring at least one measurement of flight parameters, a scoring module for attributing a first validity score to the equations by checking whether the measurement or measurements of flight parameters are a solution or solutions of the equation or equations, a scoring module for attributing a second validity score to failure scenarios involving one or more acquisition modules from the first validity scores, a determination module for determining the validity of the measurements of flight parameters from the second validity scores, consolidation module for consolidating the measurements of flight parameters, a transmission module for transmitting the consolidated measurements of flight parameters to a user device.

Abstract: An aircraft flight control system comprises a set of primary computers, each configured to compute a flight order dependent on at least one aircraft flight parameter and intended for an aircraft control surface actuator remote controller. Each computer participates in command mode within a first virtual command/monitor pair and in monitor mode within a second virtual command/monitor pair. Each computer determines a consolidated flight parameter value as a function of a flight parameter value acquired by this computer and of flight parameter values received from the other computers, using a consolidation algorithm commonly used by all primary computers to each determine a consolidated flight parameter value, and compute the intended flight order for the remote controller as a function of the consolidated flight parameter value, according to a unique computation whose result is used by the computer both when acting in command mode and when acting in monitor mode.

Abstract: Method and system for merging measurements of flight parameters of an aircraft. The system is for merging measurements of flight parameters of an aircraft, linked to one another by at least one equation, and includes at least one acquisition module for acquiring at least one measurement of flight parameters, a scoring module for attributing a first validity score to the equations by checking whether the measurement or measurements of flight parameters are a solution or solutions of the equation or equations, a scoring module for attributing a second validity score to failure scenarios involving one or more acquisition modules from the first validity scores, a determination module for determining the validity of the measurements of flight parameters from the second validity scores, consolidation module for consolidating the measurements of flight parameters, a transmission module for transmitting the consolidated measurements of flight parameters to a user device.

Abstract: An aircraft flight control system comprises a set of primary computers, each configured to compute a flight order dependent on at least one aircraft flight parameter and intended for an aircraft control surface actuator remote controller. Each computer participates in command mode within a first virtual command/monitor pair and in monitor mode within a second virtual command/monitor pair. Each computer determines a consolidated flight parameter value as a function of a flight parameter value acquired by this computer and of flight parameter values received from the other computers, using a consolidation algorithm commonly used by all primary computers to each determine a consolidated flight parameter value, and compute the intended flight order for the remote controller as a function of the consolidated flight parameter value, according to a unique computation whose result is used by the computer both when acting in command mode and when acting in monitor mode.

Abstract: The system includes a rudder bar configured to be able to be actuated by a pilot of the aircraft, a unit for automatically detecting a position value corresponding to a position of the rudder bar, an auxiliary unit for generating a trim value, a computation unit configured to generate a control value as a function of the position value of the rudder bar and of the trim value. The computation unit is configured to generate the control value according to a nonlinear kinematic relative to the position value of the rudder bar.

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: The system includes a rudder bar configured to be able to be actuated by a pilot of the aircraft, a unit for automatically detecting a position value corresponding to a position of the rudder bar, an auxiliary unit for generating a trim value, a computation unit configured to generate a control value as a function of the position value of the rudder bar and of the trim value. The computation unit is configured to generate the control value according to a nonlinear kinematic relative to the position value of the rudder bar.

Abstract: The disclosure relates to a data fusion method for fusing the measurements of a parameter, for example an aircraft flight parameter, that are taken by a plurality of sensors comprising a set of main sensors and sets of secondary sensors. The discrepancy between each main measurement and the secondary measurements is determined and a score of consistency with them is deduced therefrom. For each fault configuration of the main sensors, a first estimation, so-called conditional, of the parameter is performed and a weighting coefficient relating to this fault is calculated, taking account of the consistency scores of the main measurements. The parameter is thereafter estimated by performing a combination of the conditional measurements with the associated weighting coefficients.

Abstract: A system for computing flight commands, which comprises simplex computers coupled to form virtual command/monitor pairs. These virtual pairs send the commands computed to actuators whose controller implements an election of the pair whose command will be taken into account by the actuator.

Abstract: The disclosure relates to a data fusion method for fusing the measurements of a parameter, for example an aircraft flight parameter, that are taken by a plurality of sensors comprising a set of main sensors and sets of secondary sensors. The discrepancy between each main measurement and the secondary measurements is determined and a score of consistency with them is deduced therefrom. For each fault configuration of the main sensors, a first estimation, so-called conditional, of the parameter is performed and a weighting coefficient relating to this fault is calculated, taking account of the consistency scores of the main measurements. The parameter is thereafter estimated by performing a combination of the conditional measurements with the associated weighting coefficients.

Abstract: Disclosed is a vertical rudder control system for an aircraft. The system is comprised of a rudder trim compensation generator that is configured to generate a rudder trim compensation order to set the position of the rudder bar of the aircraft to a neutral position in which the rudder bar is controlled with nil (i.e., zero) pilot effort. The vertical rudder control system includes a flight control calculator for calculating rudder control orders to maintain the nil effort rudder bar position, with the calculation of the rudder control orders being based on a sum of the rudder bar position, determined by a detection unit, and the rudder trim compensation order. The rudder control orders are received by a rudder operating unit, which is used to deflect the vertical rudder by a deflection value based on the rudder control orders.

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 flight control system includes at least one actuator for a mobile flight surface of an aircraft, and a flight control module in communication with the actuator. The module includes a first and a second computer. Each computer calculates a control command established according to at least one predetermined law for control of the flight surface. The first computer, known as validating computer, comprises logic means adapted for comparing its control command with that of the second computer, known as master computer, and for transmitting the result of the comparison to the actuator. The actuator comprises logic means adapted for deciding, on the basis of the result, to execute or not to execute the command of the master computer. An aircraft comprising such a system is also disclosed.

Abstract: The flight control system comprises: at least one actuator (13) for a mobile surface of the said aircraft; a flight control module (12) in communication with the said actuator (13), the said module comprising at least a first and a second computer (14-1, 14-2, 14-3, 15-1, 15-2, 15-3), each computer being adapted for calculating a control command established according to at least one predetermined law for control of the said flight surface; the said actuator (13) comprising logical means (18, 19) adapted for comparing the commands of the said computers (14-1, 14-2, 14-3, 15-1, 15-2, 15-3) and for determining on the basis of these commands the action to be executed on the said mobile surface. The aircraft comprises such a system.

Abstract: A system for computing flight commands, which comprises simplex computers coupled to form virtual command/monitor pairs. These virtual pairs send the commands computed to actuators whose controller implements an election of the pair whose command will be taken into account by the actuator.

Abstract: A flight control system for an aircraft, in which control commands are transmitted between a flight control module and at least one actuator of a movable flight surface, the flight control module including at least one first and one second computer, each computer being adapted for computing, for each actuator, a control command established according to at least one predetermined law for control of the flight surface controlled by the actuator.

Abstract: The rudder control system (1) comprises means (10) for determining a compensation order for an actuator (6) of the aircraft rudder (7).

Abstract: The invention relates to a method for the transmission of data relating to the actuation of a member used to operate a vehicle, in which code words are transmitted along the length of a given channel, each of said code words resulting from the channel coding of a block of information symbols that is representative of the aforementioned data. According to the invention, at least two such successive blocks of information symbols are coded using two different codes. The invention also relates to a data transmission system that is used to implement said method.

Abstract: A flight control system for an aircraft, in which control commands are transmitted between a flight control module (12) and at least one actuator (13) of a movable flight surface, the flight control module comprising at least one first and one second computer (14-1, 14-2, 14-3, 15-1, 15-2, 15-3), each computer being adapted for computing, for each actuator, a control command established according to at least one predetermined law for control of the flight surface controlled by the actuator.

Abstract: The flight control system comprises: at least one actuator (13) for a mobile surface of the said aircraft; a flight control module (12) in communication with the said actuator (13), the said module comprising at least a first and a second computer (14-1, 14-2, 14-3, 15-1, 15-2, 15-3), each computer being adapted for calculating a control command established according to at least one predetermined law for control of the said flight surface; the said actuator (13) comprising logical means (18, 19) adapted for comparing the commands of the said computers (14-1, 14-2, 14-3, 15-1, 15-2, 15-3) and for determining on the basis of these commands the action to be executed on the said mobile surface. The aircraft comprises such a system.