Vie
David L. Vie, Union, MO US
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20130211615 | Relay Switch Control and Related Methods - Exemplary embodiments are disclosed of a relay switch control configured for connection between a power source and a load. The control includes a processor having a clock upon which an operating frequency of the processor is based, and a sealed relay operable by the processor to electrically connect or disconnect the power source and the load. The relay switch control can start power to the load through the relay after a randomized time delay determined by the processor using a value of a counter of the processor. The counter is updated as a function of cycles of the clock. | 08-15-2013 |
Gilles Vie, Paris FR
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20120146415 | POWER ALLOCATION TO DOWNHOLE TOOLS IN A BOTTOMHOLE ASSEMBLY - The present disclosure relates to a method to allocate electrical power among tools in a bottomhole assembly disposed in a wellbore. A bottomhole assembly having an electric generator, an electrical bus, a bus master, and two or more tools is provided. One or more of the two or more tools has selectable power modes. Electrical power, up to a maximum output value, is provided through the electrical bus to the two or more tools using the electric generator. Electronic components of the two or more tools are synchronized, using the bus master to select a normal power mode or a low power mode for each tool having selectable power modes. The combined power requirements of the two or more tools at any given time do not exceed the maximum output value. | 06-14-2012 |
Malcomb George Vie, Montrose GB
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20140131106 | ROTARY STEERABLE DRILLING APPARATUS - A rotary steering apparatus for a drill string in which a bending section induces a bend in a portion of the bottom hole assembly of the drill string by using the rotation of the drive shaft that drives the drill bit during normal drilling, while operating at a reduced or zero drilling mud flow rate, to drive a reduction gear that rotates a nut or cam so as to place a tension tube into tension. The tension tube abuts a flexible housing and places the flexible housing in compression. The flexible housing has a local weakening formed in it that causes it to preferentially bend in a predetermined direction. Compression in the flexible housing causes the housing to bend, which bends a portion of the bottom hole assembly so as to alter the direction of drilling. Rotation of the drive shaft at reduced or zero mud flow rate also causes the drive shaft to drive rotation of a second reduction gear the output of which rotates the bent portion of the bottom hole assembly thereby altering its tool face angle. | 05-15-2014 |
Marc Vie, Labarthe Sur Leze FR
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20150148996 | FLIGHT MANAGEMENT SYSTEM OF AN AIRCRAFT - A flight management system architecture with two separate modules is proposed. In the core module, generic functionalties relative to the flight management of the aircraft are implemented. In the supplementary module, supplementary functions are implemented. The supplementary functionalities include functionalties specific to an entity to which the aircraft belongs such as the specific aircraft model, a family of airdraft, a company, an alliance, and so on. The flight management system also includes a message exchange interface in which enables the core and supplementary modules to exchanges messages with each other. The core and supplementary modules includes corresponding core module and supplementary module interfacing functionaltities that respectively interface with generic and specific man-machine interfaces. | 05-28-2015 |
20150148998 | FLIGHT MANAGEMENT SYSTEM OF AN AIRCRAFT - A flight management system with core and supplementary modules is proposed. The core module may include generic applications that implement generic functionalities related to a flight management of the aircraft. The supplementary module may include supplementary applications that implement supplementary functionalities specific to an entity to which the aircraft belongs. The supplementary module may be divided into principal and auxiliary partitions (or entities), and the supplementary applications, also referred to as principal applications, may be implemented in the principal partition. One or more auxiliary applications may be implemented in the auxiliary partition. Each auxiliary application may be associated with one or more principal applications such that the execution of the principal application requires the associated auxiliary application to be executed. | 05-28-2015 |
20150148999 | MISSION MANAGEMENT SYSTEM OF AN AIRCRAFT - A mission management system to manage both ground and flight phases of a mission of an aircraft is proposed. The mission management system may be implemented in flight management system architecture with core and supplementary modules distinct from each other. The core module may implement a set of generic functionalities related to a flight management of the aircraft, and the supplementary module may implement supplementary functionalities specific to an entity to which the aircraft belongs. The mission management system may include a flight management unit to define and manage a flight plan and associated flight trajectory, an airport navigation unit to define and manage a ground plan and associated ground trajectory, and a mission management unit to manage a continuity between the ground and flight phases of the mission and prediction computations made by the flight management and the airport navigation units. | 05-28-2015 |
20150150095 | DATA MANAGEMENT SYSTEM OF AN AIRCRAFT - A system to manage transmissions of data between a flight management system (e.g., of an avionics type) of an aircraft and a portable electronic (e.g., of an open world type) is proposed. The data management system may be implemented in flight management system architecture with core and supplementary modules that are distinct from each other. The core module may implement a set of generic functionalities related to a flight management of the aircraft, and the supplementary module may implement supplementary functionalities specific to an entity to which the aircraft belongs. The data management system may comprise a data securing module that monitors data to be transmitted between the flight management system and the portable electronic device, and allows or prevents the data transmission based on the monitoring results. | 05-28-2015 |
Philippe Vie, Toulouse FR
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20110039073 | DAMPING SKIN FOR PROTECTING COMPOSITE PARTS - Damping skin for protecting composite parts includes a composite material having at least two superposed layers, namely a first layer formed from the juxtaposition of hollow spheres, which is intended to be applied and fixed, either directly or indirectly, to the surface of the part to be protected and a second layer covering the first and formed from a wall made of a material having plastic deformation properties. | 02-17-2011 |
Preben J.s. Vie, Stange NO
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20130316245 | BATTERY ELECTRODE MATERIAL AND METHOD FOR MAKING THE SAME - The invention concerns a method for manufacturing of a battery electrode material comprising the steps of: a) applying an electric field to at least one polymer, conductive particles and at least one solvent whereby said conductive particles become arranged between the electrodes in at least two lines that are oriented in the same direction as the electric field line, and b) stabilizing the at least one polymer, conductive particles and at least one solvent by removing at least some of said at least one solvent while maintaining the electric field in step a) whereby the at least two lines of conductive particles will remain in their position when said electric field is removed. Further, the invention concerns a battery electrode material comprising at least one polymer and conductive particles, wherein said conductive particles form at least two lines that are oriented parallel and/or co-linear to each other. | 11-28-2013 |