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Dassault Aviation patents (2015 archive)
Recent patent applications related to Dassault Aviation. Dassault Aviation is listed as an Agent/Assignee. Note: Dassault Aviation may have other listings under different names/spellings. We're not affiliated with Dassault Aviation, we're just tracking patents.
ARCHIVE: New 2018 2017 2016 2015 2014 2013 2012 2011 2010 2009 | Company Directory "D" | Dassault Aviation-related inventors
Communication system for an aircraft with an external assembly and related method
A communication system for an aircraft with an external assembly and related method are provided. The system includes a unit for receiving incoming text messages, received from the outside assembly, and sending outgoing text messages, sent to the outside assembly; a display screen and a display management station, the display management station being able to display, on the display screen, a synthesis window showing a series of incoming text messages and/or outgoing text messages, each text message containing operating information about the aircraft. ... Dassault Aviation
Drain mast and associated method
A drain mast or discharging fluids from an aircraft and associated method are provided. This drain mast includes a fairing including a base including an upstream section intended to be attached on an outer surface of the aircraft and a downstream section. ... Dassault Aviation
Device and method for plugging an end of a conduit
A plugging device for plugging an end of a conduit is provided. The plugging device includes a sealing plug to the end of the conduit, and a pin intended to be axially driven into the bore of the socket for ensuring a sealing contact between the socket and the end, comprises a driver able to drive the pin into the bore of the socket. ... Dassault Aviation
Method for determining the estimated weight of an aircraft and corresponding system
A method for determining an estimated mass of an aircraft is provided. This method includes determining a first mass of the aircraft, from characteristics of the aircraft determined before or after takeoff of the aircraft, determining, during the flight of the aircraft, a second mass of the aircraft, from a lift equation of the aircraft expressing the mass of the aircraft as a function of information representative of the load factor of the aircraft, of a lift coefficient of the aircraft, of speed information of the aircraft and of a static pressure of a mass of air passed through by the aircraft, determined from measurements by sensors of the aircraft during the flight of the aircraft, evaluating the estimated mass at said determination moment, as a function of said first and second masses.. ... Dassault Aviation
Protective module and method against torque peaks between a motor and an electric machine
A protective method is provided against torque peaks between a motor adapted for setting a shaft of the motor into rotation and an electric source adapted for electrically powering an electric assembly and including a fixed section and a rotating adapted for rotating with the shaft. The method includes a step for controlling the operation of the electric source forcing the rotary movement of the rotating section with the shaft to observe an instruction relating to the torque of the rotating section applied to the shaft of the motor, the instruction being adapted depending on at least one element characterizing a current operating state of the motor.. ... Dassault Aviation
Method of designing a system of electrical wirings for a complex system, and corresponding complex system
A method for designing a system of electrical wirings for a complex system, in particular applicable to the design of electrical wirings of an aircraft, is provided. The electrical wirings allow the flow of digital, analog or discrete data between the components of the complex system and/or the transmission of electricity to components of the complex system, the components of the complex system being grouped together in subsystems, each able to perform a predetermined function, and able to be broken down into subsystems each capable of performing a predetermined sub-function. ... Dassault Aviation
Method for determining a state of credibility of measurements made by sensors of an aircraft and corresponding system
A method for determining a state of credibility of measurements made by sensors of an aircraft is provided. This method includes determining a speed of the aircraft, from static and total pressure measurements, determining a coefficient of lift of the aircraft from an incidence measurement and from said speed, determining a weight of the aircraft, determining if an equation of lift of the aircraft is satisfied, activating a state of optimal credibility, wherein the measurements made by said sensors are considered to be reliable if the said equation of lift is satisfied, activating a state of non-optimal credibility, wherein the measurements of at least one sensor are considered to be unreliable if the said equation of lift is not satisfied.. ... Dassault Aviation
Device for displaying flight characteristics of an aircraft, aircraft instruments, and related method
A device for displaying flight characteristics of an aircraft is provided. The device includes a display for the selective display of flight characteristics of an aircraft, as a function of a state of credibility assigned to measurements from static pressure, total pressure and incidence sensors, configured for selectively displaying a primary set of flight characteristics comprising at least one flight characteristic coming from a measurement from one of said sensors, when the measurements from said sensors are deemed reliable, and a secondary set of flight characteristics, distinct from said primary set, comprising at least one secondary flight characteristic designed to replace a counterpart flight characteristic from the primary set, when the measurements from at least one sensor are deemed unreliable, said secondary flight characteristic being independent of any measurement by the or each sensor deemed unreliable done when the measurements from that sensor are deemed unreliable.. ... Dassault Aviation
Method for determining a state of credibility of measurements of an incidence sensor of an aircraft and corresponding system
A method for determining a state of credibility of measurements of an incidence sensor of an aircraft is provided. This method includes at least one coherence test between incidence measurements from said incidence sensor, and the measurements of a flight characteristic of the aircraft, distinct from the incidence. ... Dassault Aviation
System for managing a cabin environment in a platform, and associated management method
The system according to the invention comprises a mobile electronic device, at least one local base, arranged near a predefined location in the cabin, an assembly for pairing the mobile electronic device with the local base, and at least one piece of functional equipment for managing the cabin environment. The memory of the mobile electronic device stores at least one software application for controlling the functional equipment. ... Dassault Aviation
Method for detecting a failure of at least one sensor onboard an aircraft implementing wind detection, and associated system
A method for detecting a failure of at least one sensor onboard an aircraft implementing wind detection is provided. The method includes measuring an airspeed of the aircraft; measuring a geographical speed of the aircraft; determining an instantaneous wind vector, based on the measured airspeed and geographical speed; establishing an instantaneous wind variation vector, based on the determined instantaneous wind vector; projecting the instantaneous wind variation vector on the direction of the vector of an air or geographical speed of the aircraft; and determining the presence of a failure based on the obtained projection.. ... Dassault Aviation
Method for detecting a failure of at least one sensor onboard an aircraft implementing a baro-inertial loop, and associated system
A method for detecting a failure of at least one sensor onboard an aircraft implementing a baro-inertial loop is provided. The method includes implementing a baro-inertial loop including obtaining a computed vertical speed, then a short-term baro-inertial altitude, based on a double integration of the measured vertical acceleration; and developing at least one intermediate loop parameter based on a deviation between the short-term baro-inertial altitude and the pressure altitude. ... Dassault Aviation
Method for detecting a failure of at least one sensor onboard an aircraft implementing an anemo-inertial loop, and associated system
A method for detecting a failure of at least one sensor on board an aircraft is provided. The method includes implementing an anemo-inertial loop including obtaining a computed horizontal speed, based on an integration of a measured horizontal acceleration and obtainment of a short-term anemo-inertial speed from the computed horizontal speed; developing at least one intermediate loop parameter based on a deviation between the short-term anemo-inertial speed and the anemometric speed or the airspeed; and observing a failure detection parameter obtained from an intermediate parameter of the anemo-inertial loop and determining the presence of a failure on one of the sensors of the aircraft, based on the value of the observed failure detection parameter.. ... Dassault Aviation
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