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).

Abstract: This invention relates to a cooking article (1) including a metal dish (2) having a base area (20), a concave internal face (21) intended to be arranged on the side of the food to be placed in said article (1) and a convex external face (22) intended to be arranged toward a heat source, and an external coating (3) covering said external face (22), characterized in that said external coating (3) includes between 30% and 50% by weight, with respect to the entire weight of said coating (3), of at least one polyimide having a glass transition temperature Tg equal to or above 250° C. This invention also relates to a process for producing such an article (1).

Abstract: An energy protection device includes a plurality of sensors that detect a triggering situation requiring an energy protection and a control unit that actuates an energy protection function when the triggering situation is detected and also activates an autothrottle. When the control unit begins the energy protection function, an original engagement state of the autothrottle before the triggering is stored. Thus, when the aircraft returns to an operational flight domain not requiring the energy protection function, the control unit stops the energy protection function and sets an engagement state of the autothrottle based on the stored original engagement state.

Abstract: A method for guiding an aircraft during its final approach to a landing runway, whereby the aircraft is guided during its approach by aircraft position information obtained from an GNSS satellite navigation system, wherein: prior to the start of the final approach a first time tFAF is determined corresponding with the start of said final approach and a second time tTD corresponding with the landing of the aircraft on said runway, then a set of satellites is determined of the satellite navigation system for excluding from the calculation of said aircraft position information during at least a part of the time interval comprised between said first and second times; and during the final approach, the aircraft position information is determined while excluding the information corresponding with all the satellites of said set of satellites and the aircraft is guided along its final approach path by said position information.

Abstract: This invention relates to a method of indicating available services to a mobile telecommunications terminal roaming between a first geographic area and a second geographic area. When the terminal is authenticated in the second geographic area, a list which comprises the services physically available in the said second geographic area is determined and is transmitted to the terminal.

Abstract: An energy protecting device for three and four-engined aircraft includes a detecting unit configured to detect failure of each engine. A control unit is configured to provide a protective function by controlling maximum thrust of each engine. A triggering unit is configured to monitor a plurality of parameters and trigger the control unit to provide maximum thrust at predetermined conditions of the monitored parameters. An inhibiting unit is linked to the triggering unit and is configured to inhibit the protective function, when at least one of the engine on the wings of the aircraft has failed. The control unit is also configured to control the engines that have not failed to minimize thrust imbalance.

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: Method and device for aiding the piloting of an airplane during a landing phase for ensuring, during rollout on a landing runway, that in the nominal case the airplane will stop level with a selected exit, while guaranteeing that in the case of a fault the airplane will stop before the end of the runway.

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 method of aiding the piloting of an airplane ensures the availability of an automatic pilot and a thrust regulation system on board the airplane. To this end, the method includes determining first information by measuring the actual airspeed of the airplane, and this first information is used to control the automatic pilot and the thrust regulation system in a primary mode during normal operations of the airplane. When the first information is lost by becoming unavailable or unreliable, the automatic pilot and the thrust regulation system are each controlled in a secondary mode by control parameters determined using additional flight data independent from the actual airspeed of the airplane and the first information. Consequently, an alternative or redundant control is supplied for ensuring the continued operation of an automatic pilot without necessary intervention from crew members on board the airplane.

Abstract: A method and device for displaying trim information on an airplane during a take-off, for determining and displaying a precise trim setpoint which enables the pilot, by following the displayed information, to carry out a manual take-off which is optimized from the performance point of view.

Abstract: A monitoring device automatically monitors lateral guidance orders of an aircraft. The device includes a failure monitoring device for implementing comparisons between roll control orders generated by a number of equipments in order to be able to detect a failure of one of the equipments concerning the generation of lateral guidance orders of the aircraft. Additionally, the device includes a failure anticipation comparator device for analyzing inlet parameters of the equipments to determine when a failure of one of the equipments should be anticipated.

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: The present disclosure relates to a culinary article including a metal substrate having a concave inner face intended to be placed on a side in which food can be introduced into the article and a convex outer face intended to be placed facing a heat source. The inner face being coated in succession, starting from the substrate, with a hard enamel base, which is rough and contains no lead or cadmium, and then with a non-stick coating covering the hard layer. The present disclosure also relates to a method of manufacturing such an article.

Abstract: A method and a device for activating an automatic piloting mode of an aircraft are disclosed. The device can include means for engaging an automatic pilot mode, when (i) the current distance of the aircraft with respect to a reference position on the ground belongs to a determined distance range, and (ii) the current height of the aircraft is at most equal to a reference height associated to the automatic pilot mode.

Abstract: The device (1) comprises means (12, 14, 15) for automatically deactivating an energy protection function and for automatically managing an autothrottle (2), when the return of the aircraft in an operational flight domain is detected after the activation of the protection function.

Abstract: A method of determining a network parameter in a telecommunication system is disclosed. The system has a coverage area including at least two sub-areas, and also includes a User Equipment (UE) being in idle mode and being registered in at least two of these sub-areas. According to the present disclosure, a network node in the system receives from the UE a time information relating to the time periods the UE has been present in each of the at least two sub-areas it is registered in, respectively, and then this time information is utilized to determine a network parameter in the system.

Abstract: Method and device for automatically monitoring the ability of an aircraft to follow a flight trajectory with at least one turn. The monitoring device (1) includes means (6, 8, 10, 11, 14) for implementing monitorings in order to estimate the ability of the aircraft to follow at least one turn of the flight trajectory.

Abstract: Method and device for automatically monitoring lateral guidance orders of an aircraft. The monitoring device (1) includes means (8) for implementing comparisons between guidance orders generated by a number of equipments (E1, E2, E3) in order to be able to detect a failure of an equipment concerning the generation of lateral guidance orders of the aircraft (AC).

Abstract: The device (1) comprises means (10) for determining, in the case of the loss of a speed information, control parameters which are used on at least one automatic pilot of the aircraft, instead of said speed information.