Abstract: A method is for detecting a blockage of a wind vane (12) of an aircraft, with the wind vane (12) including a support (20), a paddle (22) mounted rotating relative to the support (20) along an axis (A), a motor (28) able to exert a rotational torque on the paddle (22) along the axis (A), the motor (28) being connected to a processing unit (18). The method includes applying a predetermined blockage detection torque on the paddle (22) by the motor (28); measuring at least one piece of information representative of a resistance of the paddle (22) to the predetermined detection torque; and generating, via the processing unit (18), a blocking information signal, if a predetermined condition based on the representative information is verified.

Abstract: A device for waking up a crew member resting on an aircraft includes a processing unit configured to detect current development parameters of the aircraft and/or to detect a state of consciousness of at least one other active crewmember. The processing unit is also configured to activate an apparatus for waking up the resting crew member, when at least one predetermined condition for waking up the resting crew member on one or several current parameters of the aircraft and/or on a parameter representative of the state of consciousness of the at least one other active crew member is satisfied.

Abstract: A method is for detecting a blockage of a wind vane (12) of an aircraft, with the wind vane (12) including a support (20), a paddle (22) mounted rotating relative to the support (20) along an axis (A), a motor (28) able to exert a rotational torque on the paddle (22) along the axis (A), the motor (28) being connected to a processing unit (18). The method includes applying a predetermined blockage detection torque on the paddle (22) by the motor (28); measuring at least one piece of information representative of a resistance of the paddle (22) to the predetermined detection torque; and generating, via the processing unit (18), a blocking information signal, if a predetermined condition based on the representative information is verified.

Abstract: A device for waking up a crew member resting on an aircraft includes a processing unit configured to detect current development parameters of the aircraft and/or to detect a state of consciousness of at least one other active crewmember. The processing unit is also configured to activate an apparatus for waking up the resting crew member, when at least one predetermined condition for waking up the resting crew member on one or several current parameters of the aircraft and/or on a parameter representative of the state of consciousness of the at least one other active crew member is satisfied.

Abstract: A method for detecting a failure of at least one sensor onboard an aircraft implementing a baro-inertial loop is provided. The method includes implementing a baro-inertial loop including obtaining a computed vertical speed, then a short-term baro-inertial altitude, based on a double integration of the measured vertical acceleration; and developing at least one intermediate loop parameter based on a deviation between the short-term baro-inertial altitude and the pressure altitude. The method also includes observing at least one failure detection parameter obtained from one of the intermediate parameters of the baro-inertial loop; and determining the presence of a failure on one of the sensors of the aircraft based on the value of the observed failure detection parameter.

Abstract: A method for detecting a failure of at least one sensor onboard an aircraft implementing wind detection is provided. The method includes measuring an airspeed of the aircraft; measuring a geographical speed of the aircraft; determining an instantaneous wind vector, based on the measured airspeed and geographical speed; establishing an instantaneous wind variation vector, based on the determined instantaneous wind vector; projecting the instantaneous wind variation vector on the direction of the vector of an air or geographical speed of the aircraft; and determining the presence of a failure based on the obtained projection.

Abstract: A method for detecting a failure of at least one sensor on board an aircraft is provided. The method includes implementing an anemo-inertial loop including obtaining a computed horizontal speed, based on an integration of a measured horizontal acceleration and obtainment of a short-term anemo-inertial speed from the computed horizontal speed; developing at least one intermediate loop parameter based on a deviation between the short-term anemo-inertial speed and the anemometric speed or the airspeed; and observing a failure detection parameter obtained from an intermediate parameter of the anemo-inertial loop and determining the presence of a failure on one of the sensors of the aircraft, based on the value of the observed failure detection parameter.

Abstract: A method for detecting a failure of at least one sensor onboard an aircraft implementing wind detection is provided. The method includes measuring an airspeed of the aircraft; measuring a geographical speed of the aircraft; determining an instantaneous wind vector, based on the measured airspeed and geographical speed; establishing an instantaneous wind variation vector, based on the determined instantaneous wind vector; projecting the instantaneous wind variation vector on the direction of the vector of an air or geographical speed of the aircraft; and determining the presence of a failure based on the obtained projection.

Abstract: A method for detecting a failure of at least one sensor onboard an aircraft implementing a baro-inertial loop is provided. The method includes implementing a baro-inertial loop including obtaining a computed vertical speed, then a short-term baro-inertial altitude, based on a double integration of the measured vertical acceleration; and developing at least one intermediate loop parameter based on a deviation between the short-term baro-inertial altitude and the pressure altitude. The method also includes observing at least one failure detection parameter obtained from one of the intermediate parameters of the baro-inertial loop; and determining the presence of a failure on one of the sensors of the aircraft based on the value of the observed failure detection parameter.

Abstract: A method for detecting a failure of at least one sensor on board an aircraft is provided. The method includes implementing an anemo-inertial loop including obtaining a computed horizontal speed, based on an integration of a measured horizontal acceleration and obtainment of a short-term anemo-inertial speed from the computed horizontal speed; developing at least one intermediate loop parameter based on a deviation between the short-term anemo-inertial speed and the anemometric speed or the airspeed; and observing a failure detection parameter obtained from an intermediate parameter of the anemo-inertial loop and determining the presence of a failure on one of the sensors of the aircraft, based on the value of the observed failure detection parameter.