Classifications

• • A—HUMAN NECESSITIES
  • A62—LIFE-SAVING; FIRE-FIGHTING
  • A62B—DEVICES, APPARATUS OR METHODS FOR LIFE-SAVING
  • A62B18/00—Breathing masks or helmets, e.g. affording protection against chemical agents or for use at high altitudes or incorporating a pump or compressor for reducing the inhalation effort
  • A62B18/08—Component parts for gas-masks or gas-helmets, e.g. windows, straps, speech transmitters, signal-devices
  • A62B18/082—Assembling eyepieces, lenses or vision-correction means in or on gas-masks
• • A—HUMAN NECESSITIES
  • A62—LIFE-SAVING; FIRE-FIGHTING
  • A62B—DEVICES, APPARATUS OR METHODS FOR LIFE-SAVING
  • A62B18/00—Breathing masks or helmets, e.g. affording protection against chemical agents or for use at high altitudes or incorporating a pump or compressor for reducing the inhalation effort
  • A62B18/02—Masks
• • A—HUMAN NECESSITIES
  • A62—LIFE-SAVING; FIRE-FIGHTING
  • A62B—DEVICES, APPARATUS OR METHODS FOR LIFE-SAVING
  • A62B7/00—Respiratory apparatus
  • A62B7/14—Respiratory apparatus for high-altitude aircraft
• • G—PHYSICS
  • G02—OPTICS
  • G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
  • G02B27/00—Optical systems or apparatus not provided for by any of the groups G02B1/00 - G02B26/00, G02B30/00
  • G02B27/01—Head-up displays
  • G02B27/017—Head mounted
  • G02B27/0172—Head mounted characterised by optical features
• • G—PHYSICS
  • G08—SIGNALLING
  • G08G—TRAFFIC CONTROL SYSTEMS
  • G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
  • G08G5/0017—Arrangements for implementing traffic-related aircraft activities, e.g. arrangements for generating, displaying, acquiring or managing traffic information
  • G08G5/0021—Arrangements for implementing traffic-related aircraft activities, e.g. arrangements for generating, displaying, acquiring or managing traffic information located in the aircraft
• • G—PHYSICS
  • G08—SIGNALLING
  • G08G—TRAFFIC CONTROL SYSTEMS
  • G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
  • G08G5/0047—Navigation or guidance aids for a single aircraft
  • G08G5/0056—Navigation or guidance aids for a single aircraft in an emergency situation, e.g. hijacking

Definitions

• the invention relates to a protection system for an airplane pilot intended to assist the pilot by displaying information near his eye.
• the invention aims to provide assistance to the pilot, in case of difficult situation, such as complex navigation, conditions outside the cockpit (cockpit) of the aircraft or inside the cockpit of the aircraft (in particular fire / smoke) reducing vision of visual cues on the outside of the aircraft and / or information displayed by navigational instruments inside the cockpit of the aircraft.
• the protection system comprises:
• a breathing mask adapted to supply a breathing gas to the pilot, wherein said breathing mask comprises an oxygen supply duct intended to be connected to an airplane cockpit,
• a protective window comprising a screen intended to extend between the pilot's eyes and an external space
• a security device comprising a display device and a support
• the display device is able to display, in particular in front of an eye of the pilot, information intended to assist him in piloting the airplane, and
• the support carries the display device in order to maintain the display of information facing the eye (in the field of vision) of the pilot.
• the display device provides the pilot with visual information which he could hardly dispose of or degraded.
• the protection system allows the pilot to keep both hands free to fly the aircraft.
• the display device comprises an external virtual display displaying an external virtual display in video form from either an object detector, such as a preferably infra-red camera. , a radar or a multispectral detector, to improve the vision of the pilot or to be recreated from a database.
• the protection system provides in particular to the pilot a vision outside the aircraft when the weather conditions do not allow a satisfactory direct vision, in particular the vision of the runway in case of fog.
• the external virtual display is sometimes referred to by the English acronyms EVS (Enhanced Vision System) or EFVS (Enhanced Flight Vision System).
• the display device preferably comprises a symbological display displaying by symbology flight parameters derived from navigation instruments.
• the protection system provides the pilot with a particular view of the flight parameters when the conditions inside the aircraft do not allow the pilot to see the navigation instruments or the screen representing navigational instruments.
• the symbological display device preferably comprises a graphic processing device capable firstly of receiving quantitative values of navigation instruments and secondly of generating a symbolic display of its own. .
• the protection system preferably comprises a differentiated brightness setting for the external virtual display and the symbological display.
• the protection system makes it possible to select the external virtual display and / or the symbological display.
• the pilot is effectively assisted in flying the aircraft by allowing him to select the information he needs.
• the symbological display symbologically displays flight parameters derived from navigation instruments including an artificial horizon, a speedometer and an altimeter.
• the display device advantageously displays the information in monochrome, preferably in green.
• the protection system further comprises at least one photodiode for measuring ambient brightness
• the display device has a variable display brightness
• the display brightness of the device The display varies depending on the ambient brightness measured by the photodiode.
• the display device furthermore has a display brightness setpoint, and the display brightness of the display device varies as a function of the display brightness setpoint and the display brightness. the ambient brightness.
• the protection system further comprises a storage system storing the display brightness setpoint, the display device having an off state and a lit state, and the display system. memory stores the display brightness setpoint in the off state and in the on state of the display.
• said display device constitutes an emergency display device
• the protection system further comprises a main display device able to display information on or near of, an aircraft windshield
• the protection system further comprises a source of information
• said main display device and said emergency display are both connected to said information source.
• the driver can see the information on the main display device or on the emergency device.
• the protection system further comprises an orientation detection device able to determine the position of the support and the orientation detection device acts on the display device.
• the protection system determines what information the driver is interested in and the information displayed is modified accordingly, which still effectively assists the pilot.
• the orientation detection device detects the (rotating) orientation variations of the support.
• the display device displays an information content and varies the orientation of the content with respect to the support in a manner corresponding to the variations of orientation of the support.
• the protection system moves the information content when the pilot turns his head, to give him the illusion that the content information is in the same place.
• the protection system thus provides the pilot with a virtual reality and assists him effectively in piloting.
• the orientation detection device comprises at least one inertial device.
• the inertial device comprises an accelerometric device comprising a plurality of accelerometers or a gyroscopic device with one or advantageously three axes.
• the orientation detection device preferably comprises a first inertial device linked to the support, a second inertial device intended to be linked to an aircraft and a computing device to which the first device is connected. inertial device and the second inertial device, the computing device determining the orientation of the pilot's head as a function of information transmitted by the first inertial device and the second inertial device.
• the orientation detection device comprises at least one optical device and an optical analysis device capable of determining movements.
• the optical device is advantageously an infrared system or a camera and the optical analysis device is advantageously adapted to determine a movement between two images or between an image and a reference frame in the aircraft that can be constituted by a characteristic shape of the cabin, in particular the cockpit, or by landmarks arranged for this purpose.
• the orientation detection device further comprises a camera and a camera analysis device capable of determining the orientation of the pilot's gaze with respect to the medium.
• the protection system takes into account the movements of the pilot's gaze without moving his head, which makes it possible to better determine the information useful to the pilot.
• the orientation detection device is preferably able to issue a setpoint to turn off the display device.
• the display device is turned off.
• the display device displays essential information content and optional information content
• the orientation detection device is able to issue a set of instructions to switch off or display optional information content.
• the display device displays an information content of which it is able to vary the size, and the orientation detection device is able to issue an instruction to vary the size of the information content.
• the size of the information content is reduced.
• the display device comprises a semi-reflective element and the display device comprises a projector projecting a light beam on the semi-reflective element.
• the display device may include an additional lens to focus the image.
• the shape of the semi-reflective element makes it possible to adjust the focusing distance.
• the projector comprises an emissive micro-screen.
• the projector comprises one or more light sources and a microstrip modulating the light from the light source (s), in particular a micro-LCD screen (Liquid Crystal Display), LCOS (Liquid Crystal on Silicon), DMD (Digital Micromirro Devices),
• a micro-LCD screen Liquid Crystal Display
• LCOS Liquid Crystal on Silicon
• DMD Digital Micromirro Devices
• DLP Digital Light Processing
• the display device is preferably mounted movably relative to the support between an active position intended to face an eye of the pilot and a retracted position away from the pilot's eye.
• the display device does not hinder the vision of the pilot and remains quickly usable when needed.
• the display device is preferably mounted on the support by means of a sliding system or by means of connecting rods for moving the display device between the active position. and the retracted position.
• the display device preferably extends in an interior space, separated from the outer space by the screen.
• the display device is protected, in particular ambient air may reduce the vision of the information displayed.
• the protective eyewear is adapted to be applied to the pilot's face around the eyes, the protective eyewear, and in particular the transparent screen, isolating the outer space interior space extending between the protective eyewear and the eyes of the user.
• the pilot's eyes are protected from the ambient air while having the information content provided by the display device.
• the protection assembly further comprises an adjusting device extending through the screen and able to move the display device.
• the adjusting device comprises a control wheel for manually adjusting the positioning of the display device relative to the support in the interpupillary direction, and the control wheel extends in the outer space.
• the adjusting device preferably comprises a screw-nut system.
• the display device is preferably adapted to be positioned at a distance of at least 18 millimeters from the eyes of the pilot, in order to be compatible with the wearing of eyeglasses ( or sunglasses or the like).
• the protection assembly is compatible with the wearing of eyeglasses between the display device and the face of the driver.
• the display device is in the outer space, close to the screen.
• the screen has a hole or holes opposite the display device.
• the gas in the interior space can escape through the hole and pass around the display device, to remove smoke that may be in the ambient air of the display device.
• the hole or the hole (s) has (s) an overall section preferably between 1 square millimeter and 1 square centimeter.
• the display device is preferably located at a distance of less than 10 millimeters, in particular less than 5 millimeters and preferably less than 2 millimeters, from the protective screen.
• the gas flow effectively removes smoke from the display device.
• the display device is preferably mounted to move relative to the support to move in an interpupillary direction.
• the protection system thus allows the pilot to have a better and more comfortable view of the information content provided by the display device.
• the protection system comprises an adjustment device adapted to translate the display device in the interpupillary direction.
• the adjustment device comprises a rack.
• the display device is preferably mounted to move relative to the support to move in a direction of elevation.
• the protection system preferably further comprises an adjustment device adapted to translate the display device relative to the support in a direction of elevation, perpendicular to the interpupilar direction.
• the protection system thus allows the pilot to have a still improved and more comfortable vision of the information content provided by the display device.
• the protection assembly comprises two safety devices, each safety device being intended to come into the field of vision of each driver's eye.
• the pilot has a better vision of the information content provided to him.
• the protective bezel is releasably maintained or retractable relative to the breathing mask.
• the protective window can be removed or retracted, for example in the manner of a chin strap or a motorcycle helmet visor when not useful.
• the protective window is releasably attached to the respiratory mask
• the protection system comprises an electrical conductor intended to be connected to the aircraft cockpit
• the electrical conductor comprises a first connector electrical
• said display device is connected to a second electrical connector
• the first electrical connector is automatically electrically connected to the second electrical connector when the protective eyewear is attached to the respirator.
• the protective window can be easily fixed or released from the respiratory mask.
• the respiratory mask comprises a first mode in which the breathing mask supplies the breathing gas to the pilot at substantially ambient pressure and a second mode (fire / smoke) in which the breathing mask provides the breathing gas to the pilot overpressure relative to the ambient pressure
• the safety device comprises an active mode and an inactive mode
• the pilot is protected against the intrusion of ambient gas into the breathing mask.
• the safety device is preferably automatically placed in active mode when the second mode of the respiratory mask is selected.
• the pilot has only one action to be performed to be protected against the intrusion of ambient gas into the breathing mask and to be able to access the information content provided by the display device.
• the safety device is preferably automatically placed in idle mode when the second mode of the respiratory mask is not selected.
• the transition from the active mode mode to the inactive mode comprises the stopping of the display device, in particular the transition from the active mode to the inactive mode preferably comprises the movement of the support between the active position intended to be in front of the pilot's eye and the retracted position away from the pilot's eye.
• the display device when the display device is in the retracted position, the display device is stopped.
• the protection system comprises a first electrical circuit and a second electrical circuit carried by the breathing mask and connected to the first electrical circuit by the electrical connector.
• the first electrical circuit manages the power supply and / or the electrical protection of the second electrical circuit.
• FIG. 1 illustrates a protection system according to a first embodiment of the invention, in perspective
• FIG. 2 is a front view of the protection system according to the first embodiment
• FIG. 3 illustrates a protection system according to a second embodiment of the invention, in perspective
• FIG. 4 illustrates from the side the protection system according to the second embodiment
• FIG. 5 is an exploded perspective view, along the arrow marked V in FIG. 3, a display device belonging to the protection system according to the second embodiment,
• FIG. 6 illustrates the protection system according to the second embodiment in section along the line marked VI-VI in FIG. 3,
• FIG. 7 illustrates a protection system according to a third embodiment of the invention, in perspective
• FIG. 8 illustrates on an enlarged scale part of the protection system according to the third embodiment of the invention.
• FIG. 9 illustrates the protection system according to the third embodiment with the protective window separated from the breathing mask
• FIG. 10 illustrates a protection system according to a fourth embodiment of the invention, in perspective
• FIG. 1 1 illustrates the protection system according to the fourth embodiment of face
• FIG. 12 illustrates the protection system according to the fourth embodiment in section along the line marked XII-XII in FIG.
• FIG. 13 illustrates a protection system according to a fifth embodiment of the invention, in an inactive state
• FIG. 14 illustrates the protection system according to the fifth embodiment of the invention, in an active state
• FIG. 15 illustrates an external virtual display and a symbological display provided to the pilot
• FIG. 16 illustrates a single symbology display provided to the pilot
• FIG. 17 schematically shows a protection system disposed in an aircraft cockpit. Detailed description of the invention
• FIGS. 1 and 2 illustrate a protection system 100 for an airplane pilot disposed in an aircraft cockpit 6.
• the protection system 100 comprises a breathing mask 60 and a protection assembly 50, for the pilot and the co-pilot.
• Each respirator 60 essentially comprises a facepiece 65, a regulator 66, an oxygen supply conduit 62, and an electrical conductor 64.
• the oxygen supply duct 62 is connected to an oxygen supply source 150 via a storage box 152.
• the facial piece 65 is intended to come into contact with the face 2 of a pilot, around the nose and mouth.
• the regulator 66 provides a breathing gas comprising a mixture of air and oxygen depending on the needs of the pilot.
• the protection assembly 50 essentially comprises a protective window 20 and a safety device 1.
• the protective window 20 comprises a screen 22, preferably substantially transparent, extending between the eyes 4 of the pilot and an outer space 54. More particularly, in the illustrated embodiment, the protective window 20 is applied on the pilot's face 2 around the eyes 4, the protective bezel 20 isolating an interior space 52 extending between the protective bezel 20 and the eyes 4 of the pilot.
• the security device 1 essentially comprises a display device 10 and a support 30.
• the display device 10 displays an information content 95 on a display element 12 formed by a semi-reflective element 12 arranged facing at least one eye 4 of the driver.
• the display device 10 is disposed in the interior space 52.
• the display device 10 is carried by the support 30 in order to maintain the display of the information content 95 facing the pilot's eye 4.
• the support 30 is fixed on the protective bezel 20 which is removably attached to the breathing mask 60.
• the protective bezel 20 and the breathing mask 60 are held on the face 2 of the pilot by a harness. Alternatively, only the breathing mask 60 or the protective window 20 could be held on the face by the harness.
• Fig. 15 illustrates the information content 95 displayed on the display element 12.
• the display device 10 comprises a symbology display 80 and an external virtual display 90.
• the external virtual display 90 displays a virtual vision in video form of the outside of the aircraft, particularly in front of the aircraft, to improve the pilot's vision.
• the virtual vision is provided, preferably to an information source 98, by an object detector such as a preferably infra-red camera, a radar, a multispectral detector or the like.
• an object detector such as a preferably infra-red camera, a radar, a multispectral detector or the like.
• the external virtual display 90 notably displays an airport track 92.
• the symbology display 80 symbologically displays the flight parameters from navigation instruments 88 and includes an artificial horizon 81, a speedometer 82, an altimeter 83 and a descent plane 84 to join the track.
• the artificial horizon 81, the speedometer 82 and the altimeter 83 constitute essential information content.
• the descent plane 84 constitutes optional information content.
• the speed indicator 82 is preferably an anemometer.
• the symbolic display 80 includes a graphics processing device 86 receiving quantitative values of the navigation instruments 88 and generating a clean symbolic display.
• the navigation instruments 88 supplying the quantitative values to the graphics processing device 86 are the navigational instruments of the aircraft whose information is displayed on the dashboard.
• the symbolic display 80 could display information from the avionics bus, or from instruments specific to the protection system 100.
• the protection system 100 further comprises a main display device 8 able to display an information content comparable to the information content 95 in the aircraft cockpit 6, more precisely on the windshield or near the windshield. -brise, so that the information content displayed by the main display device 8 is visible both by the pilot and the co-pilot.
• the main display device 10 is connected to the information source 98.
• the protection system comprises a first electrical circuit 142 and an electrical conductor 64.
• the safety device 10 comprises a second electrical circuit 144 including an electronic card connected to the first electrical circuit 142 by the electrical conductor 64.
• the first electrical circuit 142 is connected to a power source 140 and manages the supply and electrical protection of the second electrical circuit 144.
• the protection system 100 further comprises at least one photodiode 70 measuring the ambient brightness in the aircraft cockpit 6.
• the photodiode 70 is disposed on the protective window 20.
• the photodiode 70 is connected to the electronic card 142.
• the display device 10 varies the brightness of the information content 95 with respect to a display brightness setpoint as a function of the brightness measured by the photodiode 70.
• the protection system 100 comprises a setpoint adjustment system 72 and a storage system 74.
• the setpoint adjustment system 72 allows the pilot to vary the display brightness setpoint and the storage system stores the display brightness setpoint, so that the display brightness setpoint is retained even when the display device is turned off.
• the shape and type of the buttons of the setpoint adjustment system 72 are chosen to promote intuitive access without direct visual access to the setpoint adjustment system 72.
• the system Set point 72 is carried by the oxygen supply duct 62.
• the setpoint adjustment system 72 could be placed on the protective window 20, on the breathing mask 60 or on the mask storage box. Respiratory 152.
• the protection system 100 further comprises an orientation detection device comprising a first inertial orientation detection device 1 12, a second inertial orientation detection device 1 14, a computing device 1 16, an optical device 18, an optical analysis device 120, a camera 122 and a camera analysis device 124.
• the camera 122 is preferably an infrared system or a camera.
• the computing device 1 16, the optical analysis device 120 and the image analysis device 124 are preferably grouped together in a processing unit 125.
• the first inertial orientation detection device January 12 is linked to the support 30. In the illustrated embodiment, the first inertial orientation detection device January 12 is maintained on the protective window 20.
• the first detection device Orientation 1 12 detects the movements of the display device 10 and in particular the display element 12 relative to a fixed frame of reference.
• the first orientation detection device 12 is preferably constituted by accelerometers and / or a giroscope detecting the movements of the poster device 10 in three perpendicular directions.
• the second inertial orientation detection device 1 14 is linked to the aircraft cockpit 6.
• the second orientation detection device 1 14 detects the movements of the aircraft cockpit 6 with respect to a fixed reference system.
• the second orientation detection device 11 is preferably composed of accelerometers and / or a gyroscope detecting the movements of the display device 10 in three perpendicular directions.
• the first inertial orientation detection device 1 12 and the second inertial orientation detection device 1 14 are connected to a computing device 1 16.
• the computing device 1 16 determines the movements of the display device 10 relative to to the aircraft cockpit 6, especially the rotational movements of the display device 10 with respect to the aircraft cockpit 6, on the basis of the information transmitted to it by the first inertial orientation detection device 1 12 and the second inertial orientation detection device 1 14 .
• the optical device 1 18 is connected to the optical analysis device 120.
• the optical device 1 18 is connected to the support 30. In the illustrated embodiment, the optical device is attached to the protective window 20.
• the optical device 1 18 takes images in one or more directions and the optical analysis device 120 analyzes the images taken by the optical device 1 18.
• the optical analysis device 120 preferably directly determines the position of the display device 10 with respect to a reference linked to the aircraft cockpit 6. In a variant, the device Optical analysis 120 could determine the movements of the display device 10 from successive images. Typical shapes of the aircraft can determine the position of the display device relative to a reference linked to the aircraft cockpit, but it is preferable to have markers for this purpose in the aircraft cockpit.
• the first inertial orientation detection device 1 12, the second inertial orientation detection device 1 14 and the computing device 1 16 performing the same function as the optical device 1 18 and the optical analysis device 120, according to the invention the first inertial orientation detection device 1 12, the second inertial orientation detection device 1 14 and the computing device 1 16 may be omitted, or the optical device 1 18 and the optical analysis device 120 can be omitted.
• this redundancy is advantageously used to improve the accuracy of determination of the position of the display device 10 with respect to the aircraft cockpit.
• the orientation of the external virtual display 90 is changed according to the position of the display device 10 with respect to the aircraft cockpit 6, so that when the pilot turns the head the contents of the external virtual display it always appears in the same place with respect to a terrestrial reference system.
• the shooting device 122 is linked to the support 30. In the embodiment illustrated, the camera device 122 is secured to the protective window 20. The camera 122 provides images of the eye 4 of the pilot and the camera analysis device 124 determines the orientation of the eye 4 of the pilot relative to the face 2 of the pilot.
• the camera analysis device 124 acts on the information content 95.
• the scan analysis 124 sends a first instruction to turn off the display device 10 when it determines that the pilot does not look at the information content 95.
• the camera analysis device 124 sends a second setpoint to display or delete the optional information content, consisting of the descent plane 84 in the illustrated embodiment.
• the camera analysis device 124 sends a third setpoint to modify the size of the symbology display 80 and display it at the upper part of the display element 12 when the camera analysis device determines that the eye 4 of the pilot is directed downwards with respect to his face.
• FIG. 16 illustrates an information content 95 displayed by the modified display element 12 with respect to the information content 95 illustrated in FIG. 15 in that the external virtual display 90 is suppressed and the symbological display 80 is of reduced size and shifted towards the upper part of the display element 12.
• the display device 10 is connected to the support 30 by a first connecting rod 32 and a second connecting rod 34.
• the display device is movable between an active position illustrated in FIGS. 2 and an active position.
• the information content 95 is displayed on the display element 12 substantially opposite the eye 4 of the pilot, more precisely so that the whole of the display element 12 is included in the field of view of the pilot's eye 4.
• the field of vision is defined around a central vision point by a range of 60 degrees each side (to the left and to the right), 40 degrees up and 20 degrees down.
• inactive position 38b the display device is moved away from the pilot's eye 4 at the top of the protective window 20 in the embodiment illustrated in FIGS. 1 and 2.
• FIG. arrow 38 illustrates the displacement of the display device 10 from the active position 38a to the inactive position 38b.
• the protection system 100 includes a binary motion controller 68a with two buttons for controlling the movement of the display device between the active and inactive positions.
• the protection system 100 further comprises a substantially proportional adjustment control 68b, by potentiometer or the like.
• the adjustment control 68b makes it possible to adjust the position of the display device 10 and in particular of the display element 12 in an interpupillary direction Y.
• an electric motor 36 acts on the first rod 32.
• the display device 10 essentially comprises a projector 14 projecting a light beam on the display element 12.
• the projector comprises an emissive micro-screen.
• the second embodiment illustrated in FIGS. 3 to 6 differs essentially from the first embodiment illustrated in FIGS. 1 and 2 by adjusting the position of the display device 10 and in particular the display element 12 relative to the support. 30.
• the display device 10 is mounted on the support 30 via an intermediate element 134.
• An adjustment device 40 makes it possible to adjust the position of the display element 12 relative to the pilot's eye 4 in the interpupillary direction Y and an adjustment device 130 makes it possible to adjust the position of the display element 12 relative to the pilot's eye 4 in a direction of elevation Z perpendicular to the interpupillary direction and to the direction the look.
• the support 30 is fixed on the protective window 20 and more precisely on the screen 22.
• the adjusting device comprises a screw 44 integral with a control wheel 42 and a threaded portion acting as a nut 46 integral display device 10.
• the control wheel 42 and the screw 44 is pivotally mounted around the direction interpupillary Y relative to the intermediate element 134.
• the rotation of the control wheel 42 causes the translation of the display element 12 in the interpupillary direction Y.
• the adjustment device 40 and in particular the screw 44 s extends through the screen 22, the control wheel being located in the outer space 54 and the display device 10 being located in the inner space 52.
• the adjustment device 130 includes an upper guide lug 131, a lower guide lug 132, an upper slot 135, and a lower slot 136.
• the upper guide lug 131 and the lower guide lug 132 are integral with the liner 131.
• the upper slot 135 and the lower slot 136 are formed in the support 30 and have a complementary shape respectively of the upper guide ear 131 and the ear
• the upper guide lobe 131 is slidably mounted in the upper slot 135 and the lower guide lug 132 is slidably mounted in the upper slot 136 to translate the intermediate support 134 relative to the support 30. in the direction of elevation Z.
• An indexing hole 137 formed on the support 30 receives a rod, a ball or the like cooperating with c the intermediate element 134 to maintain the display element 12 relative to the eye 4 of the pilot in the position desired by the pilot.
• the display device 10 comprises an optical guide 13 comprising a first element 1 1 having semi-reflecting properties and a second element having semi-reflecting properties constituted by the Display element 12.
• the projector 14 projects a light beam onto the first semireflective mirror 11 which is reflected towards the display element 12.
• FIGS. 7 to 9 differs in particular from the embodiment illustrated in FIGS. 1 and 2 by adjusting the position of the display device 10 and in particular the display element 12 relative to the support 30 by via the adjusting device 40.
• the support 30 is fixed on the protective window 30 and the adjustment device 40 comprises a slide 47 on which the display device 10 is fixed.
• the slide is interposed between the support 30 and the display device 10.
• the display device 10 and in particular the display element 12 can translate in the interpupillary direction to place the display element 12 in front of the screen.
• pilot's eye 4 and thus ensure that whatever the morphology of the pilot, his pupil is positioned inside the eye box of the display device.
• the eye box is a feature of the display device 10. This is the area in which the pupil (s) must be positioned for the entire image to be seen by the driver.
• the slider 47 is provided with a rack 48 for adjusting and maintaining the desired position.
• FIGS. 7 to 9 illustrate that the protective window 20 is releasably attached to the breathing mask 60.
• the pilot can separate the protective eyewear 20 of the breathing mask 60.
• the pilot can reattach the protective eyewear 20 on the breathing mask 60.
• the electrical conductor 64 comprises a first electrical connector 16.
• the second electrical circuit 144 of the display device 10 is connected to a second electrical connector 18 by an electrical conductor 17.
• the first electrical connector 16 and the second electrical connector 18 is inserted one in the other in the assembly direction T to be connected to each other.
• the first electrical connector 16 is automatically electrically connected to the second electrical connector 18 when the protective window 20 is attached to the breathing mask 60.
• the display device 10 is located in the outer space 54.
• the display element 12 is situated at a substantially constant distance d from the screen 22.
• the distance d between the display element 12 and the screen 22 is small, advantageously less than 10 millimeters and in particular less than 2 millimeters.
• the breathing mask 60 supplies breathing gas to the interior space 52 and the regulator 66 has a pilot-selectable fire / smoke operating mode with a slight overpressure relative to the ambient pressure in the aircraft cockpit 6.
• the screen 22 has holes 24 opposite the display element 12. Thus, a flow of breathing gas flows through the holes 24 of the interior space 52 towards the outer space 54 while passing into space separating the screen 22 and the display element 12.
• Each hole 24 has a section. In the embodiment illustrated in Figures 10 to 12, the holes 24 are three in number and the same section. Alternatively, one could provide a different number of holes 24 and possibly different sections.
• the sum of the sections of the holes 24, called the overall section, is preferably between 1 square millimeter and 1 square centimeter.
• the pilot's eye 4 is remote from the screen 22 by a free distance D greater than 18 millimeters, in order to allow interposition of a pair of eyeglasses between the pilot's eye and the screen 22.
• the display device 10 being disposed in the interior space 52, the display device is interposed between the screen 22 and the pilot's eye 4, the free distance D extends therefore between the pilot's eye 4 and the display device 10.
• the display device 10 is located in the interior space 52 and is mounted on the support 30 via a sliding system 28 to move the device. display between the active position and the active position, in accordance with the arrow 38.
• the display device 10 comprises a housing 102 and the sliding system 28 comprises a first stud 103, a second stud 104, a first groove 105 and a second groove 106.
• the first stud 103 and the second stud 104 are secured to the housing 102 and are received respectively in the first groove 105 and in the first groove 105. the second groove 106.
• the first groove 103 extends substantially perpendicularly to the interpupillary direction Y and to the elevation direction Z, ie the first groove extends substantially in the direction of the gaze. .
• the second groove 106 extends substantially at an angle of 45 degrees with respect to the first groove 105.
• the invention is not limited to the embodiments illustrated by way of non-limiting indication.
• the processing set and the second orientation detection device 114 provide information for the driver display device and the display device. display of the co-driver, it could be planned to double (one for the pilot and one for the co-pilot) at least one of the graphics processing device 86, the processing unit and the second detection device 14, in particular for security reasons.

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• Devices For Indicating Variable Information By Combining Individual Elements (AREA)

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• 2015
  • 2015-04-27 FR FR1500892A patent/FR3035520A1/fr active Pending
  • 2015-10-22 FR FR1560079A patent/FR3035521B3/fr not_active Expired - Fee Related
• 2016
  • 2016-04-27 WO PCT/FR2016/050995 patent/WO2016174355A1/fr active Application Filing
  • 2016-04-27 EP EP16730447.6A patent/EP3288646A1/de not_active Withdrawn
  • 2016-04-27 CN CN201680024622.5A patent/CN107530562A/zh active Pending
  • 2016-04-27 US US15/569,366 patent/US20180304107A1/en not_active Abandoned

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