Abstract: The present invention relates to a method to secure an applicative function in a cloud-based virtual secure element implementation, said virtual secure element being intended to be used by a dedicated emulated secure element application to perform said applicative function, said implementation being supported by a user device comprising the emulated secure element application and a local secure element comprising a Public Key Infrastructure applet and by a cloud remote server having an emulated virtual secure element corresponding to the user of the user device, said user device and cloud remote server further respectively having a secure cloud library and a secure cloud front-end.

Abstract: In a method for accessing a service, a device receives data. The device gets, based upon the received data, transaction data. The device signs the transaction data by using a private key relating to a transaction processing, a signature operation result being a transaction signature. The device generates a transaction analysis result. The device stores the transaction data and the transaction signature. The device analyses whether the transaction analysis result is or is not a transaction authorization. Only if the transaction analysis result is a transaction authorization, the device gets, based upon the received data, service data. The device sends to a first external entity the service data. The device sends the transaction data and the transaction signature to either the first external entity or a second external entity.

Abstract: The present invention relates to a method to operate a contactless mobile device as a low cost secured point-of-sale, hereinafter POS device, said POS device having a non-secured operating system, a POS application installed in said non-secured operating system, an embedded secure element, a transaction proxy applet installed in said embedded secure element and a Contactless Front-End to contactless communicate with a customer mobile device having a secured transaction dedicated application.

Abstract: A de-icing device includes a hot air circuit including an inlet for hot air bled from an engine, and a duct connecting the inlet to an outlet of the circuit which opens towards the leading edge. The device also includes electrical heating means associated with the duct, and control means for controlling the heating means connected to detection means that detect the temperature of the hot air downstream of the heating means and are able to activate these if the detected temperature of the bled air is below a value corresponding to a minimum temperature required for de-icing, increased by a predetermined margin. The range of temperatures of the hot air supplied to the leading edge is lowered overall, whereas the minimum de-icing temperature is assured. Composite materials can be used near the leading edge without being damaged.

Abstract: A system for communicating via contact-less chip with an external contact-less communicating device comprises a removable chip card, a contact-less communicating chip and a terminal. The contact-less chip is carried by a flexible medium. A chip of the card is coupled, via a card connector, to the contact-less communicating chip, and a microprocessor of the terminal. The card chip is configured to act as an intermediary entity between the contact-less communicating chip and the terminal microprocessor. A card chip microprocessor exchanges data with the contact-less chip by using a first data communication protocol. The card chip microprocessor exchanges data with the terminal microprocessor by using a second data communication protocol. The terminal microprocessor is configured to send, through the card chip, to the contact-less communicating chip, data that is previously encapsulated within first communication protocol data that is itself encapsulated within second communication protocol data.

Abstract: A de-icing device includes a hot air circuit including an inlet for hot air bled from an engine, and a duct connecting the inlet to an outlet of the circuit which opens towards the leading edge. The device also includes electrical heating means associated with the duct, and control means for controlling the heating means connected to detection means that detect the temperature of the hot air downstream of the heating means and are able to activate these if the detected temperature of the bled air is below a value corresponding to a minimum temperature required for de-icing, increased by a predetermined margin. The range of temperatures of the hot air supplied to the leading edge is lowered overall, whereas the minimum de-icing temperature is assured. Composite materials can be used near the leading edge without being damaged.

Abstract: An aircraft nacelle includes a pipe, a peripheral wall, a lip connecting the pipe and peripheral wall and delimiting an air intake. A frost treatment system treats a zone extending along a longitudinal section of a point A at the peripheral wall at a point B at the pipe and includes a front frame delimiting with the lip a pipe circulating de-icing hot air. An acoustic pipe coating includes a reflective layer, at least one alveolar structure, and at least one acoustically resistive structure. The front frame includes a junction zone with the lip and/or the pipe offset toward the nacelle front relative to B. Pipes inside the lip and the pipe convey hot air from the pipe to circularly arranged discharges corresponding to B. The pipes extend beyond the junction between the front frame and the lip and/or the pipe and are delimited by at least one isolating partition.

Abstract: A system for communicating via contact-less chip with an external contact-less communicating device comprises a removable chip card, a contact-less communicating chip and a terminal. The contact-less chip is carried by a flexible medium. A chip of the card is coupled, via a card connector, to the contact-less communicating chip, and a microprocessor of the terminal. The card chip is configured to act as an intermediary entity between the contact-less communicating chip and the terminal microprocessor. A card chip microprocessor exchanges data with the contact-less chip by using a first data communication protocol. The card chip microprocessor exchanges data with the terminal microprocessor by using a second data communication protocol. The terminal microprocessor is configured to send, through the card chip, to the contact-less communicating chip, data that is previously encapsulated within first communication protocol data that is itself encapsulated within second communication protocol data.

Abstract: A system for spraying liquid (100) for a windshield (111) of an aircraft including a spray-liquid supply circuit (101), a pressurized-gas supply circuit (102) designed to purge the spray-liquid supply circuit, and at least one nozzle (114) disposed downstream from the circuits and designed to spray the spray liquid and pressurized gas on a windshield, characterized in that the system includes an auxiliary means of compression (107) ready to compress gas designed to circulate in the pressurized-gas supply circuit, the auxiliary means of compression being positioned near the nozzle. Also, an aircraft cockpit provided with at least such a spray system.

Abstract: The invention relates to an aircraft nacelle that comprises a discharge means (50) for establishing a communication between the inside of the nacelle and the outside thereof, and a junction area between two members (54, 56), and at which the two members are superimposed, both members each having a surface defining the outer surface of the nacelle on either side of the junction area, characterized in that said discharge means (50) includes a dual-portion shim (52), i.e. a first portion provided between the superimposed panels and including at least one protruding and/or recessed member for forming a passage between said panels in order to establish a communication between the inside and the outside of the nacelle, and a second portion at the level of only one panel, i.e. that located inside at the junction area, in order to protect the same against excessive temperatures.

Abstract: The invention relates to acoustic lining for an aircraft, which can cover a leading edge, such as an air inlet in the nacelle of a propulsion unit, said lining comprising: (i) from the inside outwards, a reflective layer (28), at least one cellular structure (30) and an acoustically resistive structure (32) having a pre-determined proportion of open surface; and (ii) at least one frost treatment system in the form of at least one heating layer (46) comprising open zones through which acoustic waves can pass, which co-operate at least partially with the open zones in the acoustically resistive structure. The invention is characterized in that the acoustically resistive structure (32) includes at least one structural layer (36) with openings (38) and in that said at least one heating layer (46) is disposed under the structural layer (36).

Abstract: A device for protection against icing for aircraft engines including at least one sensor, sensitive to an amount of accumulated ice, arranged in the air intake of an aircraft engine, a system for measuring the amount and comparing the amount to be predetermined threshold and a triggering system for launching a response to the detection of the crossing of the predetermined threshold, the response may be an alarm, an increase in the engine power delayed by the engine control system or the return of hot air upstream of the engine.

Abstract: The invention relates to an aircraft nacelle that comprises a discharge means (50) for establishing a communication between the inside of the nacelle and the outside thereof, and a junction area between two members (54, 56), and at which the two members are superimposed, both members each having a surface defining the outer surface of the nacelle on either side of the junction area, characterised in that said discharge means (50) includes a dual-portion shim (52), i.e. a first portion provided between the superimposed panels and including at least one protruding and/or recessed member for forming a passage between said panels in order to establish a communication between the inside and the outside of the nacelle, and a second portion at the level of only one panel, i.e. that located inside at the junction area, in order to protect the same against excessive temperatures.

Abstract: The invention relates to acoustic lining for an aircraft, which can cover a leading edge, such as an air inlet in the nacelle of a propulsion unit, said lining comprising: (i) from the inside outwards, a reflective layer (28), at least one cellular structure (30) and an acoustically resistive structure (32) having a pre-determined proportion of open surface; and (ii) at least one frost treatment system in the form of at least one heating layer (46) comprising open zones through which acoustic waves can pass, which co-operate at least partially with the open zones in the acoustically resistive structure. The invention is characterised in that the acoustically resistive structure (32) includes at least one structural layer (36) with openings (38) and in that said at least one heating layer (46) is disposed under the structural layer (36).

Abstract: An aircraft nacelle includes a pipe, a peripheral wall, a lip connecting the pipe and peripheral wall and delimiting an air intake. A frost treatment system treats a zone extending along a longitudinal section of a point A at the peripheral wall at a point B at the pipe and includes a front frame delimiting with the lip a pipe circulating deicing hot air. An acoustic pipe coating includes a reflective layer, at least one alveolar structure, and at least one acoustically resistive structure. The front frame includes a junction zone with the lip and/or the pipe offset toward the nacelle front relative to B. Pipes inside the lip and the pipe convey hot air from the pipe to circularly arranged discharges corresponding to B. The pipes extend beyond the junction between the front frame and the lip and/or the pipe and are delimited by at least one isolating partition.

Abstract: A deicing and anti-icing system for an aircraft engine pod, including an air intake provided with a lip followed by an air intake tubular part, equipped with a first sound attenuating panel, including deicing means having at least one array of resistive heating elements embedded in an insulating material, the deicing means being in the form of a mat incorporating the resistive element in the thickness of the air intake lip.

Abstract: A mobile station that includes a smart card associated with a mobile host equipment communicates by means of a protocol that is organized in several layers. These layers include at least a data transport layer of the datagram type that is adapted to transmit integral data packets of a maximum size. The transmission method carries out the step of determining the value of the maximum size of data packets that are capable of being integrally transmitted by the transport layer of the mobile host equipment, and storing that value in the card.

Abstract: A system for spraying liquid for a windshield of an aircraft includes a spray-liquid supply circuit, a pressurized-gas supply circuit designed to purge the spray-liquid supply circuit, and at least one nozzle disposed downstream from the circuits and designed to spray the spray liquid and pressurized gas on an aircraft windshield, wherein the system includes a control device able to simultaneously actuate the temporary spraying of spray liquid and of pressurized gas respectively in the spray-liquid spraying circuit and in the pressurized-gas spray circuit in such a way that a pressurized-gas spraying time is strictly greater than a spraying-liquid spraying time. For example, the control device includes a time-lag relay controlling the pressurized-gas supply circuit.

Abstract: A device for protection against icing for aircraft engines including at least one sensor, sensitive to an amount of accumulated ice, arranged in the air intake of an aircraft engine, a system for measuring the amount and comparing the amount to be predetermined threshold and a triggering system for launching a response to the detection of the crossing of the predetermined threshold, the response may be an alarm, an increase in the engine power delayed by the engine control system or the return of hot air upstream of the engine.

Abstract: A system for spraying liquid for a windshield of an aircraft includes a spray-liquid supply circuit, a pressurized-gas supply circuit designed to purge the spray-liquid supply circuit, and at least one nozzle disposed downstream from the circuits and designed to spray the spray liquid and pressurized gas on an aircraft windshield, wherein the system includes a control device able to simultaneously actuate the temporary spraying of spray liquid and of pressurized gas respectively in the spray-liquid spraying circuit and in the pressurized-gas spray circuit in such a way that a pressurized-gas spraying time is strictly greater than a spraying-liquid spraying time. For example, the control device includes a time-lag relay controlling the pressurized-gas supply circuit.