Abstract: A method and system for determining local information which is dependent on a local runway state when the aircraft is in movement on the runway in order to update, in real-time, or practically in real-time, data used by a braking assistance system, according to whether the local runway state associated with the determined local information indicates a runway deterioration relative to a reference runway state used initially.

Abstract: A method to control braking of an aircraft on a landing runway including: selecting a dummy runway state corresponding to a level of adhesion of wheels of the aircraft to a runway which is lower, over an entire speed range of the aircraft while braking on a runway, than an adhesion level of the wheels of the aircraft to the landing runway; calculating a set point of a deceleration value for the aircraft on the landing runway based on the landing runway for the selected dummy runway state, wherein the calculated set point corresponds to maximum braking value of the aircraft, and controlling the braking of the aircraft using the set point.

Abstract: A method and system for determining local information which is dependent on a local runway state when the aircraft is in movement on the runway in order to update, in real-time, or practically in real-time, data used by a braking assistance system, according to whether the local runway state associated with the determined local information indicates a runway deterioration relative to a reference runway state used initially.

Abstract: A method to control braking of an aircraft on a landing runway including: selecting a dummy runway state corresponding to a level of adhesion of wheels of the aircraft to a runway which is lower, over an entire speed range of the aircraft while braking on a runway, than an adhesion level of the wheels of the aircraft to the landing runway; calculating a set point of a deceleration value for the aircraft on the landing runway based on the landing runway for the selected dummy runway state, wherein the calculated set point corresponds to maximum braking value of the aircraft, and controlling the braking of the aircraft using the set point.

Abstract: A gas ejection cone for an aircraft turbojet, the cone including a hollow main body defining, on the outside, a radially inner skin of an annular primary flow channel, and a device generating turbulence in the primary flow limiting jet noise, mounted so as to move on the main body so as to be able to be displaced from an extracted position in which the device projects toward downstream in relation to a downstream end of the hollow main body, and a retracted position in which the device is retracted into the hollow main body, and vice versa. Further, the device includes a cylindrical support body having an axis parallel to an axis of the ejection cone, and at least one fin supported by the body.

Abstract: A method and device for aiding the piloting of an aircraft during a landing phase enables an appropriate braking mode to be selected for use with an automatic braking system. The device includes a minimum braking distance estimation device that determines a minimum braking distance required using a currently selected braking mode, and also includes an alarm device for alerting the crew, during a landing, of the selecting of an insufficient braking mode on an automatic braking system. The crew may then take an appropriate action at a mode selection input device.

Abstract: Method and device for assisting in the piloting of an aircraft during a landing. The device (1) contains means (10, 11) for calculating turnaround times depending on the use of thrust reversers upon landing, as well as means (11) to display these turnaround times.

Abstract: A method and a device for creating a continuous protected space along the path of an aircraft, in which protected space a maximum induced speed Vtc in a vortex of radius Rtc in the wake of an aircraft is decreased by increasing the radius Rtc. The method includes a preliminary step of identifying changes in the aerodynamic configurations of the aircraft liable to initiate disruptions in the wake that will have the effect of increasing the radius Rtc, —for each change in configuration determining beforehand the characteristics of propagation of the wake disturbances in the vortex, —carrying out, along the course of the aircraft, at least two configuration changes separated by a distance such that spaces, in which the effects of the wake disturbances resulting from each of the configuration changes propagated for a predetermined length of time, forms a substantially continuous protected space.

Abstract: A device and associated method for determining an airport runway state includes a device that determines a runway state and is placed on board an aircraft. The device collects measured deceleration data of the aircraft during taxiing of the aircraft on the runway. Then at least one runway state is estimated from the collected data, and the estimate is transmitted to another aircraft or to a broadcasting center during the other aircraft's runway approach.

Abstract: A gas ejection cone for an aircraft turbojet, the cone including a hollow main body defining, on the outside, a radially inner skin of an annular primary flow channel, and a device generating turbulence in the primary flow limiting jet noise, mounted so as to move on the main body so as to be able to be displaced from an extracted position in which the device projects toward downstream in relation to a downstream end of the hollow main body, and a retracted position in which the device is retracted into the hollow main body, and vice versa. Further, the device includes a cylindrical support body having an axis parallel to an axis of the ejection cone, and at least one fin supported by the body.

Abstract: Method and device for aiding the piloting of an aircraft during a landing phase. The device (1) comprises means (13) for alerting the crew, during a landing, of the selecting of an insufficient braking mode on an automatic braking system (3).

Abstract: A method and a device for creating a continuous protected space along the path of an aircraft, in which protected space a maximum induced speed Vtc in a vortex of radius Rtc in the wake of an aircraft is decreased by increasing the radius Rtc. The method includes a preliminary step of identifying changes in the aerodynamic configurations of the aircraft liable to initiate disruptions in the wake that will have the effect of increasing the radius Rtc, —for each change in configuration determining beforehand the characteristics of propagation of the wake disturbances in the vortex, —carrying out, along the course of the aircraft, at least two configuration changes separated by a distance such that spaces, in which the effects of the wake disturbances resulting from each of the configuration changes propagated for a predetermined length of time, forms a substantially continuous protected space.

Abstract: Method and device for assisting in the piloting of an aircraft during a landing. The device (1) contains means (10, 11) for calculating turnaround times depending on the use of thrust reversers upon landing, as well as means (11) to display these turnaround times.

Abstract: This invention relates to a device and a method for determining an airport runway state, as well as to the use of such a datum. With this in mind, this invention applies in particular to a device (14) for determining a runway (12) state, placed on board an aircraft (10), comprising measurement means (40i) capable of collecting at least one datum on deceleration (30, 60, 62) of the aircraft during a phase of taxiing of the aircraft on the said runway, the method comprising: a first means for estimating (42) at least one runway state information item from the said at least one measured datum; a means for transmitting (50), to at least one other aircraft (22) and/or to a broadcasting center (18), for example in approach phase, of the said at least one runway (12) state information item.