Marche, FR
Eric Marche, Saint Etienne De Crossey FR
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20140161226 | PROCESSING DEVICE AND METHOD FOR THE SPECTROMETRIC MEASUREMENT OF A PHOTON FLUX - A processing device and method for a spectrometric measurement in terms of energy of a photon flux that may be received by a photosensitive element of a detector comprises the following successive steps: converting each photon received by the photosensitive element into an electrical signal, a characteristic of which is representative of the energy of the photon considered; filtering each electrical signal with a first low-pass filter whose cutoff frequency is adjusted as a function of the photon flux, the bigger the flux, the higher the cutoff frequency; determining the characteristic of each filtered electrical signal; generating an energy spectrum for the photon flux received as a function of the characteristic of the filtered electrical signals; and filtering the energy spectrum with a second low-pass filter whose cutoff frequency is adjusted as a function of the photon flux, the bigger the flux, the lower the cutoff frequency. | 06-12-2014 |
Frederic Marche, Bailleau Armenonville FR
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20080274628 | Arrangement for Securely Connecting an Electronic Device to at Least Two Other Electronic Devices - An arrangement for connecting an accessory to a power source and to an electronic device of a vehicle. The arrangement includes: a power connector connecting the accessory to the power source, a signal connector connecting the accessory with the electronic device of the vehicle, a locking mechanism locking the power connector in position, and a locking mechanism locking the signal connector in position. The power connector lock and the signal connector lock are configured such that the signal connector can only be locked in the connected position after the power connector has been locked in the mounted position. The arrangement is suitable, for example, for an electric power steering device. | 11-06-2008 |
Hervé Marche, Toulouse FR
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20100043450 | SYSTEM FOR ATTACHING AN ENGINE TO THE STRUCTURE OF AN AIRCRAFT, SUCH AS A SAIL WING AIRCRAFT - System for attaching an engine to the structure of an aircraft, such as a sail wing aircraft. The system includes an upper beam which is firmly fixed at its front end to a first frame mounted on the aircraft structure. The upper beam is in addition firmly fixed at its median part to a second frame located to the rear of the first frame. The engine is hooked beneath the upper beam. The system is orientated in relation to a longitudinal axis X, a transverse axis Y and a vertical axis Z. Two front engine attachment points are arranged symmetrically on either side of the vertical median plane of the engine. The front attachment points include a shaft ( | 02-25-2010 |
20100108802 | SAIL WING AIRCRAFT WHICH INCLUDES AN ENGINE MOUNTED ON A PYLON - Sail wing aircraft which includes a wing ( | 05-06-2010 |
20120234970 | AIRCRAFT ENGINE ATTACHMENT PYLON - The invention relates to an aircraft engine attachment pylon, comprising a box formed by the assembly of a first spar ( | 09-20-2012 |
20120286125 | DEVICE FOR ATTACHING AN AIRCRAFT ENGINE, COMPRISING BLOCKS FOR CLAMPING AN ENGINE ATTACHMENT WITH A WEDGE EFFECT - A device for mounting an aircraft engine, including a rigid structure, an engine attachment including a connecting plate superposed to an associated connecting plate of said rigid structure, and means for mutually tightening said plates comprising at least one wedge-effect tightening block and corresponding bearing surfaces of said plates which are conformed so that, when each tightening block is applied against said bearing surfaces along a direction parallel to the plane of the contact surface between both of these plates, this block exerts by a wedge-effect a force for tightening these plates against each other along a direction perpendicular to said plane. | 11-15-2012 |
Jacques Herve Marche, Toulouse FR
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20100024387 | AIRCRAFT NACELLE WHICH INCLUDES THRUST REVERSER SYSTEM AND AIRCRAFT INCORPORATING AT LEAST ONE SUCH NACELLE - Aircraft nacelle which includes a cowl with a longitudinal axis, an engine housed in the cowl, an annular channel surrounding the engine and designed to receive a secondary flow, wherein the cowl includes a fixed part and a moving part which slides along the longitudinal axis to define a radial opening between the moving and fixed parts, a thrust reverser system which includes internal flaps mounted so that they rotate and which are designed to block the annular channel, at least partially, in the deployed position, where the moving part of the cowl includes a radial housing to receive the internal flaps in the at-rest position and where a system of applying an elastic force on each flap towards deployment is provided. Thus control over the position of the internal flaps is obtained directly by sliding the moving part. | 02-04-2010 |
20100132378 | HYDRAULIC SYSTEM FOR TRANSMISSION OF FORCES BETWEEN AN AIRCRAFT TURBOPROP AND AN ATTACHMENT DEVICE - This invention relates to a force transmission system ( | 06-03-2010 |
20110036942 | ENGINE ATTACHMENT PYLON COMPRISING MEANS OF FASTENING SPARS AND PANELS LOCATED OUTSIDE THE INNER SPACE IN THE BOX - An engine attachment pylon for an aircraft including a rigid structure including a box including an upper spar and a lower spar, connected to each other through two lateral panels. At least one of the upper and lower ends of the web of at least one of the two lateral panels includes at least one assembly cleat projecting sideways from the web towards the outside of the box, and assembled to the spar on which it bears through an attachment mechanism located outside the inner space in the box. | 02-17-2011 |
20110036943 | AIRCRAFT ENGINE ATTACHMENT PYLON COMPRISING A BOX WITH A CIRCULAR OR ELLIPTICAL SHAPED SECTION - An engine attachment pylon for an aircraft, including a rigid structure including a box formed by one or plural hollow segments. The section of at least one hollow segment is circular or elliptical in shape. | 02-17-2011 |
20110309188 | RIGID AIRCRAFT PYLON STRUCTURE IN CONTACT WITH A FUSELAGE LATERAL EXTENSION FOR ATTACHMENT - An aft part of an aircraft, including at least one engine assembly including a turbine engine and a turbine engine mounting pylon. A rigid structure of the mounting pylon includes a longitudinal central box and a connection box carried by the box and projecting from the box. The aircraft structure includes a fuselage lateral extension projecting from it, and the connection box is pressed into contact with the fuselage extension, below it, an attachment mechanism being arranged between these two entities. | 12-22-2011 |
20130097998 | THRUST REVERSER FOR AN AIRCRAFT HAVING SEMI-RECESSED TURBOFAN ENGINES - A jet propulsion unit of an aircraft, which comprises a turbofan engine ( | 04-25-2013 |
Jacques Hervé Marche, Toulouse FR
Patent application number | Description | Published |
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20100132378 | HYDRAULIC SYSTEM FOR TRANSMISSION OF FORCES BETWEEN AN AIRCRAFT TURBOPROP AND AN ATTACHMENT DEVICE - This invention relates to a force transmission system ( | 06-03-2010 |
20110309189 | RIGID AIRCRAFT PYLON FITTED WITH A RIB EXTENSION FOR TAKING UP THE MOMENT IN THE LENGTHWAYS DIRECTION - An engine assembly for an aircraft, including a rigid structure including a box rib extension protruding from a box of the structure, in a line of separation, towards a fuselage of the aircraft. The extension supports a first attachment in a position separating it from a second attachment in the line of separation. The first and second attachments enable the moment being exerted in a lengthways direction of the turbine engine to be transmitted jointly. | 12-22-2011 |
20110314788 | Aircraft Turbine Engine And Use Of Such A Turbine Engine - The invention relates to an aircraft turbine engine and to the use of such a turbine engine. According to the invention, the turbine engine (la) comprises a means for shifting the axis (la-la) of the blower ( | 12-29-2011 |
20120006936 | ENGINE ASSEMBLY FOR AIRCRAFT INCLUDING A MODULAR RIGID STRUCTURE FOR MOUNTING PYLONS - An aircraft engine assembly including a mounting pylon including a rigid structure fitted with a central box, together with a forward extension and a rear extension each including an attached upper organ supported on an upper surface of the central box, and an attached lower organ supported on a lower surface of the front end. The forward and rear extensions support at least a part of the first fasteners interposed between the rigid structure and a turbine engine. | 01-12-2012 |
Patrice Marche, Meylan FR
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20080286777 | Method of Determining the Diversity of T Lymphocytes in a Biological Sample - The invention relates to the field comprising the diagnosis of possible immune system disorders and the analysis of immune responses. In particular, the invention relates to a method of determining the diversity of T lymphocytes in a biological sample, based on the molecular analysis of the structure of the junctions resulting from the recombination rearrangement V(D)J of element δRec-1 with an AJ gene. More specifically, the invention relates to a method of analyzing the combinatorial diversity and/or the junctional diversity of the excision circles (TREC) resulting from the rearrangement of δRec-1, in order to determine the heterogeneity of a given population of T lymphocytes. | 11-20-2008 |
20130137085 | Method for Real-Time Measurement of the Individual Secretions of a Cell - The present invention relates to a method for real-time measurement of the secretion of at least one compound by at least one individual cell, comprising: | 05-30-2013 |
Pierre Marche, Malay Le Grand FR
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20120020799 | OPTIMIZED AERODYNAMIC PROFILE FOR A TURBINE BLADE, IN PARTICULAR FOR A ROTARY WHEEL OF THE THIRD STAGE OF A TURBINE - When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance of the point under consideration from a first reference plane P | 01-26-2012 |
20120070298 | OPTIMIZED AERODYNAMIC PROFILE FOR A TURBINE BLADE, IN PARTICULAR FOR A ROTARY WHEEL OF THE SECOND STAGE OF A TURBINE - When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance of the point under consideration from a first reference plane P | 03-22-2012 |
Stephane Marche, Toulouse FR
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20120035841 | AIRBORNE SEPARATION ASSURANCE SYSTEM AND REQUIRED TIME OF ARRIVAL FUNCTION COOPERATION - Methods and systems are provided for enhancing the functionality of an airborne separation assurance system (ASAS) by modifying it to cooperate with a required time of arrival (RTA) functionality. The system comprises an autopilot configured to execute a trajectory of an aircraft and a flight management system (FMS) in operable communication with the autopilot. The FMS includes a required time of arrival (RTA) system that is configured to determine an RTA aircraft trajectory of the aircraft based on a required time of arrival of the aircraft at a waypoint along the flight plan. The system also includes an airborne separation assurance system (ASAS) in operable communication with the RTA and is configured to determine a spacing trajectory based on a spacing interval from a first reference aircraft. | 02-09-2012 |
20120078450 | DISPLAY INFORMATION TO SUPPORT CLIMB OPTIMIZATION DURING CRUISE - Methods and systems are provided for executing a single continuous altitude change by an aircraft to cruise altitude using an electronic flight bag via a flight management system. The method comprises the determination of an altitude change in a flight plan during the cruise phase of the flight plan. Based on the altitude change and a mathematical model of the aircraft an optimum vertical trajectory profile or the aircraft is determined from which an angle of attack (AOA) and a thrust is derived to achieve the optimum vertical trajectory. From the AOA and the thrust, the required aircraft control variables are determined that may be applied to the engines and the control surface actuators of the aircraft. | 03-29-2012 |
Thierry Marche, La Chapelle Basse Mar FR
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20100304080 | ELASTIC COMPOSITE - An elastic composite includes a first nonwoven, a second nonwoven, and two elastic films sandwiched between the first and second nonwoven. The elastic composite also includes a lateral edge portion where the first nonwoven is bonded to the second nonwoven, a lane between the elastic films that is free of the elastic films, and a first bond joining the first nonwoven to the elastic film, and a second bond joining the second nonwoven to the elastic film. The elastic composite may be used as a component of a disposable garment. | 12-02-2010 |
Thierry Marche, La Chapelle Basse Mer FR
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20100135600 | AUTOMATIC GRIPPING DEVICE WITH EXTREMELY FLEXIBLE HOOKS - An automatic gripping closure device comprising a first element with hooks comprising a first base band and at least two first hooks originating from the first band and placed in at least one row of first hooks ( | 06-03-2010 |
20130029554 | METHOD FOR IMPARTING ELASTICITY TO A NON-WOVEN MATERIAL / ELASTOMER LAMINATE - Method for imparting elasticity to a laminate comprising at least one elastic film having a width and at least one ply of non-woven material secured to the film, particularly through interposition of a bonding material, particularly glue, which comprises the following steps in which: | 01-31-2013 |
20130177741 | RESILIENT LAMINATE HAVING INCREASED STRENGTH AGAINST STRESSES - The invention relates to a resilient laminate comprising, in a vertical direction, a stack of at least one nonwoven layer and a ply consisting of a part or integral part attached to the at least one nonwoven layer, in particular by means of an adhesive such as glue, the ply comprising at least one resilient film area and at least one so-called rigid film area made of a material that is less resilient than the material of the resilient area, in particular an area made of a non-resilient material, the ply being produced by the coextrusion of the at least one resilient film and the at least one rigid film, such that an interface is formed therebetween, characterized in that, from a cross-sectional view, the curve or line formed by the interface between the two films comprises at least one first substantially rectilinear segment, and at least one second substantially rectilinear segment which is angled relative to the at least one first segment. The curve or line formed by the interface between the two films extends from a point (P | 07-11-2013 |
20140245575 | AUTOMATIC GRIPPING DEVICE WITH EXTREMELY FLEXIBLE HOOKS - An automatic gripping closure device comprising a first element with hooks comprising a first base band and at least two first hooks originating from the first band and placed in at least one row of first hooks ( | 09-04-2014 |
20150074956 | HOOK FASTENER - The present invention relates to a hook fastener including a base strip and a field of hooks, each hook comprising a stem and a cap, said cap including at least one lateral overhang, and each hook being further delimited by two opposing substantially planar surfaces, wherein the overhang comprises a swelling located at a distance from the stem so that the thickness of the overhang increases in said swelling, the bottom surface of the overhang forming a cavity for receiving filaments. | 03-19-2015 |
Thierry Marche, La Chapelle Bassee Mer FR
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20120022490 | RESILIENT LAMINATE AND REINFORCED NON-WOVEN FABRIC - Hook part of a self-gripping hook and loop closure, in particular for a nappy, comprising a hook element comprising a sheet from which hooks protrude and a laminated element fixed to the hook element, the laminate extending in a transverse direction between two respective left and right lateral edges, comprising a layer fixed to at least one layer ( | 01-26-2012 |
Thierry J. Marche, La Chapelle Basse Mer FR
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20130123738 | ABSORBENT ARTICLES WITH HOOK AND LOOP FASTENING SYSTEMS - A hook for use on a male fastening material in a fastening system, wherein the hook is configured for use with a fibrous material as a female fastening material in the fastening system. | 05-16-2013 |
Yves Frederic Emile Marche, Cabourg FR
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20130188335 | ARM WEARABLE ILLUMINATING DEVICE - A arm wearable illuminating device comprises a bendable carrier, which is a bendable long-sheet-shape body; a plurality of illuminating element, which are evenly installed along long-axis direction of one side of the bendable carrier, and illuminate outwardly from the mounted surface; a transparent protective unit, which wraps the said bendable carrier and the said illuminating elements, and allows the emitting light from the illuminating elements transmitting through the transparent protective unit and displaying luminance; and a power supply device, which provides the electric power to the illuminating element for emitting light and controls the on-off status; thereby, the invention of the arm wearable illuminating device is operatively bendable for mounting on the arm, and is operatively stretchable for dismounting off the arm. | 07-25-2013 |