Abstract: A method and system allowing fully autonomous automatic take-off using only images captured by cameras on the aircraft and avionics data. The system includes an image capture device on the aircraft to take a stream of images of the runway, image processing modules to estimate, on the basis of the streams of images, a preliminary current position of the aircraft on the runway and to assign a preliminary confidence index to the estimate. A data consolidation module can determine a relevant current position of the aircraft on the runway by consolidating data originating from the image processing modules with inertial data to correct the estimate of the preliminary current position and determine a relevant confidence index using a current speed of the wheels of the aircraft to refine the preliminary confidence index. A flight control computer can control and guide aircraft take-off.

Abstract: A method and system allowing fully autonomous automatic take-off using only images captured by cameras on the aircraft and avionics data. The system includes an image capture device on the aircraft to take a stream of images of the runway, image processing modules to estimate, on the basis of the streams of images, a preliminary current position of the aircraft on the runway and to assign a preliminary confidence index to the estimate. A data consolidation module can determine a relevant current position of the aircraft on the runway by consolidating data originating from the image processing modules with inertial data to correct the estimate of the preliminary current position and determine a relevant confidence index using a current speed of the wheels of the aircraft to refine the preliminary confidence index. A flight control computer can control and guide aircraft take-off.

Abstract: A heating article includes a substrate having two opposite surfaces, at least one of which is opaque, and a heat-stable coating arranged on the opaque surface. The heat-stable coating includes an at least two-color decoration having continuous tones and being provided in the form of a continuous or discontinuous layer.

Abstract: Provided is an article, particularly culinary, comprising a cast iron support having two opposite sides. The article comprises a vitreous coating in the form of at least a continuous layer of a sol-gel material comprising a matrix formed from at least a metal polyalkoxylate and at least a reactive or unreactive silicone oil, the layer of sol-gel material being deposited directly on one at least of the sides of said support, and the side provided with a vitreous coating has a surface roughness Ra ranging between 3 and 15 ?m with a peak count per centimeter RPc ranging between 50 and 200. A method for manufacturing such an article is also provided.

Abstract: A method and device for aiding piloting of an aircraft during an approach phase for the purpose of landing. The device includes a guidance system for guiding the aircraft according to a first guidance mode during an initial phase upstream of a transition point, then guiding the aircraft according to a second guidance mode during a terminal phase between the transition point and the landing, the device further including a computing system for automatically computing the coordinates of the transition point, the guidance system also configured for automatically disabling the second guidance mode upstream of the transition point.

Abstract: A method and a system for controlling an emergency descent of an aircraft. The system (1) includes a unit (2) for detecting an emergency situation, a unit (11) for calculating a usual emergency descent command, a unit (12) for calculating a limited emergency descent command, a selection unit (14) configured for selecting the usual emergency descent command or, if application conditions are met and if the limited descent command is less than said usual emergency descent command and greater than a regulation emergency descent command, selecting the limited emergency descent command, and a unit (4) for application, to the aircraft, of the selected emergency descent command.

Abstract: A heating article includes a substrate having two opposite surfaces, at least one of which is opaque, and a heat-stable coating arranged on the opaque surface. The heat-stable coating includes an at least two-color decoration having continuous tones and being provided in the form of a continuous or discontinuous layer.

Abstract: A heating article includes a substrate having two opposite surfaces, at least one of which is opaque, and a heat-stable coating arranged on the opaque surface. The heat-stable coating includes an at least two-color decoration having continuous tones and being provided in the form of a continuous or discontinuous layer. A method for manufacturing such an article includes applying a decoration composition on the opaque surface of the article to form a moist decoration layer, and then heating the moist decoration layer to form a decoration having the form of one of a continuous or discontinuous layer.

Abstract: A method is described for aiding the piloting of an airplane by ensuring availability of an automatic pilot that is normally controlled as a function of speed information of the airplane when the speed information is lost. The method includes detecting a loss of the speed information of the airplane. In response to the detection of the loss of the speed information, the method includes determining flight data of the airplane being independent from the speed information of the airplane, determining control parameters from the flight data, and controlling the automatic pilot based on the control parameters and without the speed information of the airplane. The automatic pilot includes an automatic piloting system or a flight director.

Abstract: A method and a system for controlling an emergency descent of an aircraft. The system (1) includes a unit (2) for detecting an emergency situation, a unit (11) for calculating a usual emergency descent command, a unit (12) for calculating a limited emergency descent command, a selection unit (14) configured for selecting the usual emergency descent command or, if application conditions are met and if the limited descent command is less than said usual emergency descent command and greater than a regulation emergency descent command, selecting the limited emergency descent command, and a unit (4) for application, to the aircraft, of the selected emergency descent command.

Abstract: Energy protection device for an aircraft. The device (1) comprises units (12, 14, 15) for automatically deactivating an energy protection function, if a return of the aircraft to an operational flight domain is detected after the activation of this protection function, and for automatically managing an autothrust (2), if at least one of the following conditions is satisfied: a relaxing of a control member is detected, and the angle of attack of the aircraft is below a predetermined threshold.

Abstract: A method and system for managing automatic guidance of an aircraft during a complete engine failure. Said system includes means for monitoring engines so as to be able to detect a complete failure of the engines; means for detecting whether the aircraft is in flight; means for detecting whether the aircraft is in a different guidance mode from a guidance mode configured to make the aircraft descend with a reduced engine thrust and a fixed speed; and control means for automatically bringing guidance means of the aircraft into a guidance configuration compatible with the situation associated with the complete failure of the engines.

Abstract: A device comprising a display unit which is configured to display, on a screen of the cockpit of the aircraft, a pitch bar illustrating a pitch order and means for adapting the direct gain of the pitch law used to the effective manual behavior of the pilot in order to obtain a homogeneous response from the aircraft.

Abstract: The display device (1) comprises means (3) for correcting an acceleration value used for displaying on a screen (7) a speed trend of the airplane, making it possible to zero a speed trend symbol (11) when the Mach number of the airplane does not vary.

Abstract: Energy protection device for an aircraft. The device (1) comprises units (12, 14, 15) for automatically deactivating an energy protection function, if a return of the aircraft to an operational flight domain is detected after the activation of this protection function, and for automatically managing an autothrust (2), if at least one of the following conditions is satisfied: a relaxing of a control member is detected, and the angle of attack of the aircraft is below a predetermined threshold.

Abstract: An automatic landing method and device for an aircraft on a runway with strong slope. The device includes means to automatically transmit, a runway slope value to an automatic piloting system of the aircraft, and said automatic piloting system uses the slope value to automatically manage the flare phase upon landing.

Abstract: A monitoring device for automatically monitoring the ability of an aircraft to follow a flight trajectory with at least one turn includes a series of elements that estimate the ability of the aircraft to follow at least one turn of the flight trajectory. For example, a turn radius and limit speed for each of the upcoming turns in a flight plan (or a partial portion of the upcoming turns) are analyzed by comparing to a current speed of the aircraft to determine if there will be any risk of excursion outside the flight plan path, such that warnings can be emitted to a crew of the aircraft to take corrective action before the turns are performed. Consequently, required navigational performance maneuvers can be assured before the beginning of the turns in the flight plan.

Abstract: A method and device for aiding piloting of an aircraft during an approach phase for the purpose of landing. The device includes a guidance system for guiding the aircraft according to a first guidance mode during an initial phase upstream of a transition point, then guiding the aircraft according to a second guidance mode during a terminal phase between the transition point and the landing, the device further including a computing system for automatically computing the coordinates of the transition point, the guidance system also configured for automatically disabling the second guidance mode upstream of the transition point.

Abstract: A device comprising a display unit which is configured to display, on a screen of the cockpit of the aircraft, a pitch bar illustrating a pitch order and means for adapting the direct gain of the pitch law used to the effective manual behavior of the pilot in order to obtain a homogeneous response from the aircraft.

Abstract: The present invention relates to a heating article (1) which includes a substrate (2) having two opposite surfaces (21, 22), at least one of which is opaque, and a heat-stable coating (3) arranged on said opaque surface (21). According to the invention, the heat-stable coating (3) includes an at least two-colour decoration (31) having continuous tones and being provided in the form of a continuous or discontinuous layer, and the heating article has been cured at a temperature of more than 300° C. The present invention also relates to a method for manufacturing such an article (1).