Abstract: A method and a device for protecting an aircraft in the flight phase, said aircraft exhibiting several configurations of slats and flaps, comprises the following steps: determining, for at least one configuration of slats and flaps, of a limit angle of incidence beyond which the aircraft runs a risk of stalling, determining a gain factor as a function of the normal acceleration of the aircraft, comparing the current angle of incidence of the aircraft with the limit angle of incidence weighted by the gain factor, and, emission of an alert indicating that the aircraft runs a risk of stalling, if the current angle of incidence of the aircraft is greater than the limit angle of incidence weighted by the gain factor.

Abstract: A method for assisting in the locating of a first aircraft includes a step of emission by the first aircraft of an identifier and of a time-stamped position reading, said method further including: the reception and the storage by at least one second aircraft of the identifier and of the time-stamped position reading, and the downloading by the second aircraft, after its landing, of the identifiers and of the time-stamped position readings to a database on the ground, and, in case of disappearance of the first aircraft, the determination of the last known position of the first aircraft based on the time-stamped position readings stored in the database on the ground.

Abstract: System for detecting wake turbulence (SDWT) of a first aircraft, which can be embedded onboard a second aircraft, comprising: first means (DET1) for determining the roll (Roll2) of the second aircraft; second determination means (DET2) of an envelope (CRollRef) of reference roll curves which is representative of a wake turbulence created by the first aircraft; means (COMP) for comparing, over a sliding window, the roll (Roll2) of the second aircraft and the envelope (CRollRef) of reference roll curves; and alarm means (AL) for forewarning the pilot of the second aircraft of the detection of wake turbulence of the first aircraft when the said comparison is below a resemblance threshold (SS).

Abstract: A method and a device for protecting an aircraft in the flight phase, said aircraft exhibiting several configurations of slats and flaps, comprises the following steps: determining, for at least one configuration of slats and flaps, of a limit angle of incidence beyond which the aircraft runs a risk of stalling, determining a gain factor as a function of the normal acceleration of the aircraft, comparing the current angle of incidence of the aircraft—with the limit angle of incidence weighted by the gain factor, and, emission of an alert indicating that the aircraft runs a risk of stalling, if the current angle of incidence of the aircraft is greater than the limit angle of incidence weighted by the gain factor.

Abstract: A method for assisting in the locating of a first aircraft includes a step of emission by the first aircraft of an identifier and of a time-stamped position reading, said method further including: the reception and the storage by at least one second aircraft of the identifier and of the time-stamped position reading, and the downloading by the second aircraft, after its landing, of the identifiers and of the time-stamped position readings to a database on the ground, and, in case of disappearance of the first aircraft, the determination of the last known position of the first aircraft based on the time-stamped position readings stored in the database on the ground.

Abstract: Method, device and item of equipment for filtering alarms originating from a windshear detection system embedded in an aircraft being able to emit an alarm. The aircraft has at least one sensor allowing the acquisition of a flight parameter. The device includes: units for the calculation of the second derivative of the flight parameter, units for the calculation of the absolute value of the second derivative of the flight parameter, units for the comparison of the absolute value of the second derivative of the flight parameter with a threshold C1, units for evaluating whether the absolute value of the second derivative of the flight parameter exceeds the threshold C1 over a duration greater than a time threshold T, and units for suppressing the alarm originating from the windshear detection system.

Abstract: System for detecting wake turbulence (SDWT) of a first aircraft, which can be embedded onboard a second aircraft, comprising: first means (DET1) for determining the roll (Roll2) of the second aircraft; second determination means (DET2) of an envelope (CRollRef) of reference roll curves which is representative of a wake turbulence created by the first aircraft; means (COMP) for comparing, over a sliding window, the roll (Roll2) of the second aircraft and the envelope (CRollRef) of reference roll curves; and alarm means (AL) for forewarning the pilot of the second aircraft of the detection of wake turbulence of the first aircraft when the said comparison is below a resemblance threshold (SS).

Abstract: The invention relates to a method, a device and an item of equipment for filtering alarms originating from a windshear detection system embedded in an aircraft being able to emit an alarm. The aircraft has at least one sensor allowing the acquisition of a flight parameter. The device according to the invention includes: means (302), (402) for the calculation of the second derivative of the flight parameter, means (303), (403) for the calculation of the absolute value of the second derivative of the flight parameter, means (304), (404) for the comparison of the absolute value of the second derivative of the flight parameter with a threshold C1, means for evaluating whether the absolute value of the second derivative of the flight parameter exceeds the threshold C1 over a duration greater than a time threshold T, and means for suppressing the alarm originating from the windshear detection system (350), (450).

Abstract: The invention relates to a device for remote measurement of the properties of the atmosphere, more particularly a device used to detect atmospheric turbulence. The device operates on the lidar principle, using the backscattering of a laser beam by the air. The device comprises a laser emission source (1), optical means (5) for collecting a backscattered beam (3) that is backscattered by targets illuminated by the emission source (1), the backscattered beam (3) being substantially centerd about the wavelength of the emission source (1), and means (9) for generating interference fringes (24) resulting from the backscattered beam (3). The device also includes a spatial filter (11) allowing only a central spot of the interference fringes to be seen and, at the center of the spatial filter (11), a mask for blocking off the center of the central spot and more particularly the Mie line of the backscattered beam.

Abstract: The invention relates to a device for remote measurement of the properties of the atmosphere, more particularly a device used to detect atmospheric turbulence. The device operates on the lidar principle, using the backscattering of a laser beam by the air. The device comprises a laser emission source (1), optical means (5) for collecting a backscattered beam (3) that is backscattered by targets illuminated by the emission source (1), the backscattered beam (3) being substantially centred about the wavelength of the emission source (1), and means (9) for generating interference fringes (24) resulting from the backscattered beam (3). The device also includes a spatial filter (11) allowing only a central spot of the interference fringes to be seen and, at the centre of the spatial filter (11), a mask for blocking off the centre of the central spot and more particularly the Mie line of the backscattered beam.