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| 20110051078 | INFORMATIVE EYEGLASSES - The invention relates to informative eyeglasses ( | 03-03-2011 |
| 20120327508 | DEVICE FOR SHORT-DISTANCE PROJECTION AT A REASONABLY LARGE ANGLE WITH ZOOM AND FOCUSING - The invention proposes a short-distance front projection system, that is to say with a wide angle, occupying a small volume and offering a possibility of focusing as well a zoom function. It makes it possible to obtain images with a diagonal greater than 2 metres, the whole of the optical system being at least 50 cm from the plane of the image. This projector is constructed on the basis of three optical elements: an ocular, an afocal lens system and a final group forming an objective intended to form the intermediate image in front of the mirror. | 12-27-2012 |
| 20140092482 | Optical Guidance Device and Method of Manufacturing Such a Device - An optical guidance device for optical guidance of a light beam has a first part, in a transparent material, adapted for propagating the light beam by successive reflections. This first part comprises an extraction section comprising at least one microstructure comprising a plane surface adapted to enable the rays of the light beam striking the plane surface to emerge from the guidance device. The device also comprises a second part, in a material substantially identical to that of the first part, comprising a section comprising at least one microstructure with a shape complementary to that or those of the extraction section. The device also has a layer of adhesive assembling the first and second parts in such a way that any microstructure of the extraction section is separated from its complementary microstructure by a transparent medium of substantially constant thickness. | 04-03-2014 |
| 20140334777 | OPTICAL GUIDE WITH SUPERIMPOSED GUIDANCE ELEMENTS AND MANUFACTURING METHOD - An optical guide comprises an injection zone intended to inject into the optical guide a light signal and an extraction zone intended to provide the light signal after transport by the optical guide. The optical guide comprises, in a superposed manner, at least two guidance elements. In a zone situated between the injection zone and the extraction zone, the guidance elements are partially separated from one another by a semi-reflective coating of length, in the direction or propagation of the light signal in the optical guide, dependent on a minimum angle of incidence of the light signal and on the thickness of at least one of the guidance elements that the semi-reflective coating separates. | 11-13-2014 |
| 20150268401 | OPTICAL DEVICE AND METHOD FOR MANUFACTURING SUCH A DEVICE - An optical device includes an optical guide adapted for propagating a light beam by successive total internal reflections and an injection device adapted for injecting the light beam into the optical guide via an injection section. A polarising material is present between the optical guide and the injection device at the injection section. The injection device includes a prism and an assembly formed by a quarter-wave plate and curved mirror, the injection device being arranged so that a light beam reflected by the polarising material in the direction of the curved mirror passes through the quarter-wave plate and is then reflected by the curved mirror in the direction of the polarising material and passes through the quarter-wave plate again. | 09-24-2015 |
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| 20140327883 | DEVICE FOR DETERMINING AT LEAST ONE SIGHT PARAMETER OF A SUBJECT IN A PLURALITY OF VIEWING DIRECTIONS - Device for determining at least one sight parameter of a subject, includes stimulation elements for stimulating the sight of the subject in a predetermined viewing direction, elements for ophthalmological measurement of at least one sight parameter of a subject, the elements for ophthalmological measurement having at most one optical measurement axis for each eye, at least one optical conjugation system, arranged between the ophthalmological measurement apparatus and the right eye and/or left eye of a subject, and a system for aligning the optical conjugation system, so as to optically conjugate a point Y and a point E, the point Y intended to coincide with the optical centre of rotation of the eye concerned, the point E being situated on the optical measurement axis, so as to align the image of the optical measurement axis with the ocular axis of the right or left eye in a plurality of viewing directions. | 11-06-2014 |
| 20140362345 | BINOCULAR MULTIPLEXING METHOD AND DEVICE - A binocular multiplexing device for a single-channel ophthalmological instrument for objective measurement of at least one vision parameter of a subject, the ophthalmological instrument including elements for generating a single light beam, elements for collecting a measurement beam by reflecting and/or refracting the light beam against the subject's eye and a sensor associated with the single measurement channel. The binocular multiplexing device includes optical separation first elements for receiving an image beam originating from a stimulus target and separating the image beam into a right and left ocular stimulation beam; optical switching elements for switching the single light beam selectively onto a right or left monocular light beam's optical path to form, after reflection and/or refraction by the eye in question, a right, respectively left, ocular measurement beam, and optical combination elements for superimposing the right, respectively left, ocular stimulation beam, and the right, respectively left, monocular light beam. | 12-11-2014 |
| 20150109578 | DEVICE AND METHOD FOR DETERMINING AT LEAST ONE OBJECTIVE EYE REFRACTION PARAMETER OF A SUBJECT DEPENDING ON A PLURALITY OF GAZE DIRECTIONS - Device and method for determining an objective eye refraction parameter of a subject depending on a plurality of gaze directions, the device includes elements for ophthalmologically measuring an objective eye refraction parameter of a subject, and elements of visual stimulation of variable proximity and intended to stimulate the visual accommodation of the subject for first and second proximity values. The device includes opto-mechanical alignment elements for carrying out a first optical alignment of the optical axis of measurement on an eye axis in a first measuring position corresponding to a first angle of lowered viewing associated with a first proximity value to take a first measurement of an objective eye refraction parameter of the subject, and a second alignment of the optical axis of measurement on the eye axis in another measuring position corresponding to another angle of lowered viewing associated with another proximity value to take a second measurement. | 04-23-2015 |
| 20150146168 | DEVICE AND METHOD FOR MEASURING OBJECTIVE OCULAR REFRACTION AND AT LEAST ONE GEOMETRIC-MORPHOLOGICAL PARAMETER OF AN INDIVIDUAL - Disclosed is a device for measuring ocular refraction and a geometric-morphological parameter of an individual, including: a gaze-stimulating target placed so as to stimulate the gaze of the individual in a posture associated with a proximity value and a sight axis; an illuminating system able to generate at least one illuminating beam in the direction of the eyes of the individual; an image-capturing system; and a computer able to receive at least one first image captured by the image-capturing system. According to the invention, the image-capturing system is able to acquire an image of part of the face surrounding the eyes of the individual, and the computer is able to extract, from the acquired image, a first measurement of a glazing parameter and a first measurement of objective ocular refraction by refraction of the illuminating beam on the eyes of the individual in the given posture. | 05-28-2015 |
| 20150374224 | DEVICE AND METHOD FOR MEASURING AT LEAST ONE OBJECTIVE OCULAR REFRACTION CHARACTERISTIC OF A PATIENT FOR A PLURALITY OF VISUAL RANGES - A device for measuring the objective ocular refraction of a patient for a plurality of visual ranges, which includes a variable proximity optical sight system capable of selectively generating a first target and a second target and an image-capturing device having an optical measurement axis intended for being aligned with a line of sight of the patient, the image-capturing device being capable of capturing a first ocular refraction image when the first target is activated and a second ocular refraction image when the second target is activated. The image-capturing device and the optical sight system are arranged such that the optical measurement axis and the optical sight axis are arranged such that the optical measurement axis and the optical sight axis are contained in a single plane and the optical measurement axis is tilted at an angle alpha between +5 degrees and +85 degrees relative to the horizontal. | 12-31-2015 |
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| 20130064268 | METHOD FOR MONITORING AT LEAST TWO TEMPERATURE SENSORS OF A TURBOMACHINE - A method for monitoring at least two temperature sensors of a turbomachine that is aligned along a reference plane, the two temperature sensors being located in the same transverse plane of the turbomachine, the method including detecting the stoppage of the turbomachine; waiting for a period at least equal to a predetermined threshold period; measuring the temperature with each of the two temperature sensors; comparing the two temperatures measured. | 03-14-2013 |
| 20140129193 | METHOD OF CONSTRUCTING A BEHAVIOR MODEL OF AN AIRPLANE ENGINE - A method of constructing a behavior model ( | 05-08-2014 |
| 20140236415 | SYSTEM FOR MONITORING A MEASUREMENT CHAIN OF A TURBOJET ENGINE - A method and a system for monitoring a measuring chain arranged to collect over time measures relating to a turbojet engine of an aircraft, the system including a processor configured to build a health indicator of the measuring chain based on counting transitions between successive health words defining a validity score of corresponding successive measures. | 08-21-2014 |
| 20150285093 | METHOD FOR MONITORING AN IGNITION SEQUENCE OF A TURBOMACHINE ENGINE - A method for monitoring an ignition sequence of an engine, in particular a turbomachine engine, including the following steps: (i) defining an ignition time of the engine for a defined starting parameter, (ii) comparing the ignition time of the engine defined in this way with a reference ignition time expected for a reference engine and for this starting parameter, (iii) deducing an indicator of the bringing into operation of the engine, (iv) repeating steps (i) to (iii) for this starting parameter, for each bringing into operation of the engine of the sequence, and (v) on the basis of the change in the indicator, generating a degradation alert for the ignition sequence of the engine. | 10-08-2015 |
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| 20130304283 | Method for controlling the piloting of an aircraft - A method for controlling the piloting of an aircraft comprising the steps of receiving at least one first instruction for modification of a current velocity vector of the aircraft, determining a target velocity vector of the aircraft, on the basis of said at least one first instruction received, and determining, on the basis at least of said target velocity vector, at least one actuation command intended for at least one actuator of the aircraft in order to modify the movement of the aircraft according to said at least one first instruction received. | 11-14-2013 |
| 20140114506 | METHOD FOR ASSISTING IN THE PILOTING OF AN AIRCRAFT DURING A LANDING AND PILOTING ASSISTANCE SYSTEM SUITABLE FOR IMPLEMENTING THIS METHOD - A method for assisting in the piloting of an aircraft during a landing on a landing area on the ground. The method includes the following steps: (1) during a landing phase, while the landing area on the ground is visible from the aircraft: displaying, on a screen of the cockpit of the aircraft, a target corresponding to this landing, overlaid on a view outside the aircraft; receiving from a pilot a command to modify this target and displaying the duly modified target; and receiving a command to validate a value of the target by a pilot; (2) automatically determining an aircraft flight trajectory as a function of the aircraft's current position and of the value of the target validated by the pilot and storing this trajectory; and (3) guiding the aircraft along the stored trajectory. Also a piloting assistance system suitable for implementing this method is disclosed. | 04-24-2014 |
| 20140236399 | Method and device for estimating an unwanted pitch moment of an aircraft, and applications to the pitch control of the aircraft - A method and device for estimating an unwanted pitch moment of an aircraft, and applications to the pitch control of the aircraft. The device estimates an unwanted pitch moment, which can be used to form a compensation command which is added to a standard deflection command with the aim of producing an automatic, active compensation, in real time, for the unwanted pitch moment of the aircraft. | 08-21-2014 |
| 20150019050 | METHOD AND DEVICE FOR DISPLAYING IN REAL TIME A PITCH INSTRUCTION ON AN AIRCRAFT DURING MANUAL PILOTING - A device comprising a display unit which is configured to display, on a screen of the cockpit of the aircraft, a pitch bar illustrating a pitch order and means for adapting the direct gain of the pitch law used to the effective manual behavior of the pilot in order to obtain a homogeneous response from the aircraft. | 01-15-2015 |
| 20150032299 | AUTONOMOUS AND AUTOMATIC LANDING METHOD AND SYSTEM - A system and method are disclosed for automatic landing of an aircraft on a landing runway, including an on-board video camera intended to take images of the ground, image processor to extract from these images visual features of the landing runway, guidance system determining guidance commands of the aircraft to bring it into a nominal approach plane and to align it with the axis of the landing runway, from the respective positions of the visual features of the landing runway, in at least one of the images, where the guidance commands are supplied to a flight control computer. | 01-29-2015 |
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| 20120219415 | METALLIC ANNULAR CONNECTION STRUCTURE FOR AIRCRAFT TURBOMACHINE - A metallic annular connection structure between two parts for an aircraft turbomachine, with an arbitrary half-section including two primary branches and a base forming a first U opening up in the radial direction from a longitudinal axis, and two secondary branches forming a second U with one of the two primary branches opening up in the longitudinal direction. The primary and secondary branches and the base of the first U are made in a single piece. | 08-30-2012 |
| 20120226409 | SYSTEM AND METHOD FOR MEASURING FATIGUE FOR MECHANICAL COMPONENTS OF AN AIRCRAFT AND AIRCRAFT MAINTENANCE METHOD - A system for measuring fatigue of a component of an aircraft subject to mechanical stresses includes: a plurality of stress sensors mounted on the component, each sensor being configured to detect a predetermined mechanical stress threshold and to deliver a data signal representative of exceeding of the threshold; and a mechanism for recording the data and the sensors configured to detect different stress thresholds so as to make it possible to calculate, on the basis of the data recorded by the system, an estimation of fatigue of the component due to the mechanical stresses. It is thus possible to optimize overhaul of the components. | 09-06-2012 |
| 20130014515 | LINK BETWEEN THE EXHAUST CASING AND A STRUCTURAL RING OF THE FAN DUCT OF A JET ENGINEAANM Bellabal; Francois RobertAACI FontainebleauAACO FRAAGP Bellabal; Francois Robert Fontainebleau FRAANM Seize; GuilhemAACI Corbeil EssonnesAACO FRAAGP Seize; Guilhem Corbeil Essonnes FRAANM Vincent; Thomas Alain ChristianAACI PalaiseauAACO FRAAGP Vincent; Thomas Alain Christian Palaiseau FR - An assembly including an outer ring of an exhaust casing, a structural ring of an external duct of a fan channel and of a two-flow jet engine that is concentric relative to the outer ring of the exhaust casing, and at least one first and second linking arm or rod forming a hyperstatic link by being attached by one end to the outer ring of the exhaust casing and, by the other end, to the structural ring. The link formed by the first linking arm or rod is configured to break when a predetermined load is exceeded, and the second linking arm or rod is configured to form a force-transmission path between the rings when the link is broken. | 01-17-2013 |
| 20130195640 | DUAL-FLOW TURBOMACHINE FOR AIRCRAFT, INCLUDING STRUCTURAL MEANS OF RIGIDIFYING THE CENTRAL CASING - A turbomachine for an aircraft including a mechanism forming a case fitted in a rear extension of an inner ferrule of an intermediate casing, and positioned around a central casing. The mechanism includes a structural upstream ferrule assembled on the inner ferrule and defining a front portion of a surface internally delimiting a secondary vein, and a main case extending on the upstream ferrule towards the rear. The turbomachine further includes a structural mechanism rigidifying the central casing, surrounded by the case, and extending towards the rear between the upstream ferrule and the central casing on which these mechanisms are assembled. | 08-01-2013 |
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| 20120119056 | BEAM FOR SUSPENDING A TURBOSHAFT ENGINE FROM AN AIRCRAFT STRUCTURE - A beam for suspending a turboshaft engine from an aircraft structure, including a first attachment mechanism configured to be secured to the aircraft structure and at least one second attachment mechanism configured to be secured to the engine. The beam is at least partially made from a metal-matrix composite material including reinforcing fibres. In one embodiment, the beam takes a form of a circle arc. | 05-17-2012 |
| 20130099051 | TURBOSHAFT ENGINE ATTACHED TO A PYLON OF THE FUSELAGE OF AN AIRCRAFT BY A FAILSAFE SUSPENSION SYSTEM - A suspension system including a front suspension plane located at an intermediate turboshaft engine casing and connecting same to a pylon, a rear suspension plane located at an exhaust casing of the turboshaft engine and connecting same to the pylon, and a failsafe intermediate suspension plane located between the front and rear planes and including at least one connecting rod connecting the turboshaft engine having a structural outer casing to the pylon, the connecting rod mounted on the turboshaft engine with a predetermined clearance that renders the connecting rod inoperable while the suspension system of the rear plane is operating. The connecting rod is advantageously arranged between the outer casing and the pylon, and an element made of a flexible material is combined with the connecting rod to create the predetermined clearance by an elastically deformable nature thereof. | 04-25-2013 |
| 20140102114 | IN-LINE REMOVABLE HEAT SHIELD FOR A TURBOMACHINE SUSPENSION YOKE - Heat shield device for a means of suspending an engine from an aircraft, the said device comprising panels able to be fixed to the said means, at least one of the said panels extending radially in the direction of the axis of the engine, characterized in that it further comprises a component configured to be fixed to the said engine and comprising a groove shaped in such a way that the lower end of the said panel can be inserted into it. | 04-17-2014 |
| 20140112770 | TURBOJET ENGINE COLD STREAM FLOW PATH SUSPENDED FROM THE EXHAUST CASE BY RADIAL CREVICE MOUNTS AND LINK RODS - A bypass turbojet engine including a cylindrical cold stream flow path supported by link rods which are attached to a cylindrical outer shell ring of an exhaust case at attachment points. The attachment points for the exhaust case are crevice mounts including lugs that extend radially from the outer shell ring, a bore of the crevice mounts being directed in a direction of generatrices of the outer shell ring. | 04-24-2014 |
