Abstract: A method that recommends capturing a stream of images of the landing zone, using a first imaging system to calculate position information for the landing zone on the basis of at least one real image of the stream, using an autopilot system to determine a current position of the landing zone at the current calculation instant, using a second imaging system to verify the presence of a landing zone at the current position in the real image, and generating an alarm if the presence is not found.

Abstract: A method and a device for determining and displaying a flyaway distance for a rotorcraft in the event of an engine of the rotorcraft failing, and while taking account of the height of waves being overflown by the rotorcraft. The method includes a first determination for determining a flyaway distance of the rotorcraft in the event of a failure of an engine and under current flying conditions, a second determination for determining a maximum altitude of the waves being overflown by the rotorcraft and displaying the flyaway distance and the maximum altitude on a display instrument of the rotorcraft indicating the relative height of the rotorcraft or else its altitude. A safety margin is preferably added to the maximum altitude of the waves, or else to the flyaway distance of the rotorcraft.

Abstract: A haptic alert mechanism. The mechanism includes an actuator. At least one arm of a movable stopping piece is connected to the actuator. A spring box is provided with an enclosure containing a pre-stressed torsion spring, said spring box being mounted to be movable in rotation about the axis of rotation. The enclosure includes at least one lug that is mounted to be movable in rotation about said axis of rotation. A finger of the torsion spring passes through an elongate orifice in a front flank of the enclosure to form a movable, resilient stop that is overridable.

Abstract: A haptic alert mechanism. The mechanism includes an actuator. At least one arm of a movable stopping piece is connected to the actuator. A spring box is provided with an enclosure containing a pre-stressed torsion spring, said spring box being mounted to be movable in rotation about the axis of rotation. The enclosure includes at least one lug that is mounted to be movable in rotation about said axis of rotation. A finger of the torsion spring passes through an elongate orifice in a front flank of the enclosure to form a movable, resilient stop that is overridable.

Abstract: A directional lighting system fitted to an aircraft and comprising firstly a light source mounted on a motor-driven support and secondly a control device serving to control the motor-driven support. According to the invention, such a directional lighting system comprises a selector member for selecting a pointing target that is to be pointed to, a camera for acquiring a plurality of images of the surroundings outside the aircraft, image processor means for identifying the selected pointing target, a calculation unit configured to calculate the current coordinates of the pointing target, and a servocontrol member of the control device for servocontrolling the position of the motor-driven support to occupy an angular orientation as determined by the calculation unit.

Abstract: A directional lighting system fitted to an aircraft and comprising firstly a light source mounted on a motor-driven support and secondly a control device serving to control the motor-driven support. According to the invention, such a directional lighting system comprises a selector member for selecting a pointing target that is to be pointed to, a camera for acquiring a plurality of images of the surroundings outside the aircraft, image processor means for identifying the selected pointing target, a calculation unit configured to calculate the current coordinates of the pointing target, and a servocontrol member of the control device for servocontrolling the position of the motor-driven support to occupy an angular orientation as determined by the calculation unit.

Abstract: A method and a device for avoiding an object by detecting its approach to an aircraft. After detecting an object in the vicinity of an aircraft and detecting its approach, a first track for the object and a second track for the aircraft are estimated from successive first states for the object and successive second states for the aircraft. Thereafter, a minimum distance (dm) between the first track and the second track is estimated and a warning is triggered as soon as the minimum distance is less than a first threshold so as to warn a crew of the aircraft of a risk of collision. Finally, if the minimum distance is less than a second threshold, an avoidance maneuver is performed automatically by the aircraft in order to move away from the first track, and thereby avoid any risk of collision with the object.

Abstract: An electric control device having manipulation means. The electric control device has a first measurement system and a second measurement system respectively taking a first measurement and a second measurement of the current position of the manipulation means. A processor unit compares the first and second measurements in order to generate a control signal as a function of said current position, said processor unit considering that the manipulation means are in a neutral position when the first and second measurements do not correspond to the same position for the manipulation means.

Abstract: A method and a device for determining and displaying a flyaway distance for a rotorcraft in the event of an engine of the rotorcraft failing, and while taking account of the height of waves being overflown by the rotorcraft. The method includes a first determination for determining a flyaway distance of the rotorcraft in the event of a failure of an engine and under current flying conditions, a second determination for determining a maximum altitude of the waves being overflown by the rotorcraft and displaying the flyaway distance and the maximum altitude on a display instrument of the rotorcraft indicating the relative height of the rotorcraft or else its altitude. A safety margin is preferably added to the maximum altitude of the waves, or else to the flyaway distance of the rotorcraft.

Abstract: A device for assisting the piloting of a rotorcraft in order to pilot a rotorcraft during an approach stage preceding a stage of landing on a rotorcraft landing area. Such a device includes in particular a camera for taking a plurality of images of the environment of the rotorcraft along a line of sight, looking at least along a forward direction Dx of the rotorcraft, and processor for identifying in at least one image from among said plurality of images at least one looked-for landing area.

Abstract: A method and a device for avoiding an object by detecting its approach to an aircraft. After detecting an object in the vicinity of an aircraft and detecting its approach, a first track for the object and a second track for the aircraft are estimated from successive first states for the object and successive second states for the aircraft. Thereafter, a minimum distance (dm) between the first track and the second track is estimated and a warning is triggered as soon as the minimum distance is less than a first threshold so as to warn a crew of the aircraft of a risk of collision. Finally, if the minimum distance is less than a second threshold, an avoidance maneuver is performed automatically by the aircraft in order to move away from the first track, and thereby avoid any risk of collision with the object.

Abstract: A method that recommends capturing a stream of images of the landing zone, using a first imaging system to calculate position information for the landing zone on the basis of at least one real image of the stream, using an autopilot system to determine a current position of the landing zone at the current calculation instant, using a second imaging system to verify the presence of a landing zone at the current position in the real image, and generating an alarm if the presence is not found.

Abstract: An electric control device having manipulation means. The electric control device has a first measurement system and a second measurement system respectively taking a first measurement and a second measurement of the current position of the manipulation means. A processor unit compares the first and second measurements in order to generate a control signal as a function of said current position, said processor unit considering that the manipulation means are in a neutral position when the first and second measurements do not correspond to the same position for the manipulation means.

Abstract: A device for assisting the piloting of a rotorcraft in order to pilot a rotorcraft during an approach stage preceding a stage of landing on a rotorcraft landing area. Such a device includes in particular a camera for taking a plurality of images of the environment of the rotorcraft along a line of sight, looking at least along a forward direction Dx of the rotorcraft, and processor means for identifying in at least one image from among said plurality of images at least one looked-for landing area.

Abstract: A method of determining the longitudinal air speed VairX and the longitudinal ground speed VsolX of a rotary wing aircraft depending on the exposure of the aircraft to the wind, the aircraft flying at a speed of advance Va. The method making it possible to determine characteristic speed curves for the aircraft depending on the longitudinal speed of the relative wind to which the aircraft is subjected, and then during a flight and depending on the actions of the pilot of the aircraft, to deduce the longitudinal ground speed VsolX and the longitudinal air speed VairX to be applied to the aircraft depending on variations in the longitudinal speed of the relative wind to which the aircraft is subjected.

Abstract: A flight control method and system for a rotary wing aircraft. When the longitudinal speed UX of the aircraft is greater than a first threshold speed Vthresh1, a first mode of operation of the method enables flight to be performed while maintaining track relative to the ground, the flight setpoints of an autopilot being a ground course angle TKsol, a forward speed Va, a flight path angle P, and a heading ?. When the longitudinal speed UX is less than a second threshold speed Vthresh2, a second mode of operation enables flight to be performed while maintaining heading, the flight setpoints being the longitudinal speed UX, a lateral speed VY, a vertical speed WZ, and the heading ?.

Abstract: A flight control system for a rotary wing aircraft, the aircraft following a track Tsol, relative to the ground with a ground course angle TKsol, a forward speed Va, a flight path angle P, and a heading ?, the aircraft having one or more rotary wings provided with blades of collective pitch and of cyclic pitch that are variable about respective pitch axes and that are capable of performing movements in rotation and in translation. The flight control system has two control members each provided respectively with at least one movement axis A, B, C, D, and an autopilot for generating control signals. An action on one of the control members relative to one of the movement axes A, B, C, D gives rise independently to a modification to the forward speed Va, to the ground course angle TKsol, or indeed to the flight path angle P by means of the autopilot.

Abstract: A method and a system for engaging hovering flight for a rotary wing aircraft. A first mode of operation makes it possible, while the longitudinal speed UX of the aircraft is greater than a first threshold speed Vthresh1 to approach a stop position S while maintaining track relative to the ground, the flight setpoints of an autopilot being a ground course angle TKsol, a deceleration rate Ga for the forward speed Va of the aircraft, a flight path angle P, and a heading ?. A second mode of operation makes it possible, when the longitudinal speed UX is less than a second threshold speed Vthresh2, to engage hovering flight at the stop position S while maintaining heading, the flight setpoints being the longitudinal speed UX, a lateral speed VY, a vertical speed WZ, and the heading ?, the speeds UX, VY, and WZ being reduced progressively to zero speed.

Abstract: A method of determining the longitudinal air speed VairX and the longitudinal ground speed VsolX of a rotary wing aircraft depending on the exposure of the aircraft to the wind, the aircraft flying at a speed of advance Va. The method making it possible to determine characteristic speed curves for the aircraft depending on the longitudinal speed of the relative wind to which the aircraft is subjected, and then during a flight and depending on the actions of the pilot of the aircraft, to deduce the longitudinal ground speed VsolX and the longitudinal air speed VairX to be applied to the aircraft depending on variations in the longitudinal speed of the relative wind to which the aircraft is subjected.

Abstract: A method and a system for determining an angular velocity in turning for a rotary wing aircraft in order to make turns that are coordinated relative to the ground or else relative to the air and in order to manage the transition between ground coordination and air coordination while taking account of the wind to which the aircraft is subjected. The method serving to determine an angular velocity in yaw using an anticipation value and a correction value on the basis in particular of speeds of advance of the aircraft relative to the ground and relative to the air of its lateral acceleration and of its lateral load factor.