• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Lighting system for an aircraft, comprising at least one optical acquisition device, at least one long-range projector each comprising at least one light source (3a, 3b), servo means (4), and a means for controlling (5) the light sources (3a, 3b), based on the data received from the optical acquisition device and a data network of the aircraft so that the lighting system produces at least one beam of light. in an adaptive manner with respect to the flight and taxi phases of the aircraft so as to illuminate at least one predefined area of the space around the aircraft.
    公开号:FR3069528A1
    申请号:FR1757213
    申请日:2017-07-28
    公开日:2019-02-01
    发明作者:Christian Tsao
    申请人:Zodiac Aero Electric SAS；
    IPC主号:
    专利说明:


    Lighting system for an aircraft.
    The invention relates to the technical field of the lighting system, and more particularly the lighting systems on board an aircraft.
    Runway lighting systems on board aircraft currently include searchlights associated for all or part of a flight phase among taxiing (“taxi” in English), turning (“runway turn-off”), takeoff ( “Take-off” in English) and landing (“landing” in English).
    These headlights are separate and fixed in different places of the aircraft, in particular on a landing gear leg, generally of the front landing gear, as well as on the wings, at the leading edge, in the root of the 'wing on the fuselage, under the ventral fairing or under the wing for certain retractable projectors.
    At night, during the different flight phases, these different searchlights are used successively or simultaneously to allow the pilot to identify the space in which he must operate.
    Each flight phase is thus associated with one or more light beams whose intensity distribution and pointing are different and adapted to the visibility needs of pilots. Figure 1 schematically illustrates a possible arrangement of the different light beams as well as a part of the associated projectors. It should be noted that the representation is made in the plane of the aircraft and therefore does not show the differences in direction of pointing relative to this plane. The light beams during the landing phase are referenced L. The light beams during the taxiing phase are referenced T, the light beams during the turn phase are referenced R and the light beams during the takeoff phase are referenced TO.
    During the approach phase, the landing lights (“landing light” in English), referenced L in FIG. 1, point along the descent trajectory (rectilinear trajectory) so as to illuminate the place where the airplane must touch the ground. This is where the pilot should look.
    In the touchdown phase of the runway, before the main landing gear wheels touched the runway, the aircraft attitude varied and pitched slightly. The aircraft’s trajectory changes and rounds to be tangent to the runway.
    The touchdown phase being very brief, no beam, until now, is specifically dedicated to this phase.
    Just after the touchdown phase, the nose gear comes into contact with the ground. The take-off lights (take-off light in English) then take over with a pointing almost parallel to the ground. These searchlights illuminate the runway in front of the aircraft.
    The takeoff and landing phase beams are characterized by a type of beam whose spatial distribution of light intensity is identical and collimated on the pointing direction; at the end of the runway for the take-off phase and along the descent slope for the landing phase.
    During the taxiing phase, taxiing (“taxi light” in English) and turning (“runway turn off light” in English) are used on taxiways (“taxiway” in English) to leave or access the track. The lighting during this phase is characterized by a light distribution strongly spread horizontally in order to identify an obstacle around the aircraft, mainly in front of the cockpit (“Taxi Light”) and in front of the wings (“runway turn off light”). ).
    These beams must remain concentrated vertically and folded towards the ground to minimize the glare of the runway personnel crossing these two types of beam.
    These lighting systems have significant drawbacks. First of all, the searchlights are fixed and therefore cannot follow the angular variations in the incidence of the aircraft during the landing and takeoff phases, in particular during the variations in direction or force of the prevailing winds. Due to the significant variations in attitude of the aircraft, with regard to the pointing accuracy required, the lighting thus produced on the runway can be very variable in efficiency and in pointing.
    The use of a large number of separate projectors also has the disadvantage of a large size and weight, critical parameters in aeronautics.
    In addition, the electrical consumption and the number of locations necessary to ensure satisfactory lighting with regard to the required performance create a significant layout and electrical supply constraint.
    In addition, the simultaneous ignition of the landing and take-off beams degrades the visual perception of the pilots because of the light backscattering of the mist in the humid air which decreases the contrast of the areas observed. Indeed, the mirror projectors used in aeronautics reflect only about half of the light generated by the mirror to form the beam. The rest of the light generated by the source does not undergo any reflection and leaves the plane directly at a very wide solid angle. Part of this lost light passes between the pilot and the beam used to illuminate the scene. When the weather is dry, this beam of lost light does not illuminate any airborne particles in the pilot's field of vision. On the other hand, during periods of mist, the particles in suspension in the pilot's field of vision are illuminated, creating a more or less dense veil of backscattered light. This backscatter degrades the contrast and can dazzle the pilot, especially when the fog is dense.
    There is therefore a need for a lighting system for an aircraft comprising a limited number of searchlights compared to the existing one while providing at least equal lighting.
    The subject of the invention is a lighting system for an aircraft, comprising at least one optical acquisition device, at least one long-range projector each comprising at least one light source, control means, and a means of control of light sources as a function of the data received from the optical acquisition device and from an aircraft data network so that the lighting system produces at least one light beam adaptively with respect to the phases of flight and taxiing of the aircraft so as to illuminate at least one predefined area of space around the aircraft.
    The long-range headlamp may be capable of illuminating an aircraft runway at a distance of at least 300m.
    The long-range projector may include a high-speed scanning device provided with at least two rotating reflecting surfaces, the axes of rotation of which are orthogonal and arranged so that the beam at the output of the light source is reflected successively on the one then the other of the reflecting surfaces.
    The long-range projector can comprise at least one centered optical system with variable focal length or at least one centered optical system with fixed focal length whose focal plane is occupied by a light source, as well as means for moving the light source so that the direction of the light beam can be inclined relative to the axis of the centered optical system and / or moved perpendicular to the focal plane so that the opening of the beam can be enlarged.
    The long-range projector can include a striated and prismatic lens, disposed at the outlet of the centered optical system and making it possible to generate at least one light beam.
    The long-range projector can comprise a set of at least two phosphors, each capable of absorbing the light emitted by a light source and of re-emitting white light.
    The light source can be a laser type source or a laser type light source obtained by combining a monochromatic light source of the red laser type, a monochromatic light source of the green laser type and a source monochromatic blue laser light.
    The invention also relates to a method for controlling a lighting system comprising the following steps:
    we acquire an image of the scene in front of the plane with at least one optical acquisition device, we perform pattern recognition on the acquired image of the scene in order to distinguish the various objects present, in particular the runway, signaling at ground, and possible obstacles, flight information is obtained from the aircraft data network, the current flight phase is determined based on the information acquired and a predetermined model, at least one beam d is determined. lighting to be switched on as well as their direction and spread as a function of the determined flight phase and of the objects recognized in front of the aircraft, the directions are set for the direction of the light sources, of the servo means and, when applicable, of the means for moving at least one light source as a function of the lighting beams to be switched on as well as their directions and their spreads.
    The flight information can include at least one value among the speed, the altitude, the attitude angle, the thrust, the thrust reversal state, the ground contact of the wheels, the position of the edges d 'attack and shutters.
    To determine at least one light beam to be switched on as well as their direction and spread, for each light beam to be switched on, the vertical angle, the horizontal angle and the pointing direction of the beam can be determined as a function of predetermined values of the coordinates and of the extent of the area to be illuminated so that the beam illuminates a predefined area of the space around the aircraft, then the values determined can be corrected as a function of the flight data comprising at least the respective positions of the runway and the aircraft.
    The lighting system has the advantage of being a multifunctional and versatile system, configurable in extent and direction from very long range areas beyond traditional landing functions thanks to the use of laser technology up to '' to areas near taxiing of the aircraft.
    The system also has the advantage of enslavement and adaptation of the beams in the vertical and horizontal directions through the use of an optical acquisition device and a control method for monitoring and analysis of the areas to be lit.
    The lighting system is also advantageous compared to the existing one by the reduction in glare and stray light due to the use of a collimated laser beam and by the reduction in the number of equipment necessary for production. different light beams from an aircraft.
    Finally, the invention can be used in addition to traditional lighting by being integrated into an LED, HID or Halogen type lighting system. In this case, the invention is subject to pointing relative to the image processing from the integrated optical acquisition device. If the servo is not operational then the pointing of the laser light beam will be judiciously predetermined according to a default pointing.
    Other objects, characteristics and advantages of the invention will appear on reading the following description, given solely by way of nonlimiting example and made with reference to the appended drawings in which:
    FIG. 1 illustrates an arrangement of the various light beams on an aircraft according to an embodiment of the state of the art,
    FIG. 2 illustrates the different lighting beams generated by the lighting system according to an embodiment of the invention,
    FIG. 3 illustrates a first embodiment of a lighting system according to the invention,
    FIG. 4 illustrates a second embodiment of a lighting system according to the invention,
    FIG. 5 illustrates a third embodiment of a lighting system according to the invention, and
    - Figure 6 illustrates the different stages of a method of controlling the lighting system according to the invention.
    The lighting system 1 according to the invention makes it possible to replace all of the searchlights associated with the different flight phases of the aircraft with at least one long-range searchlight controlled in direction of aiming (orientation) and in intensity distribution luminous (extended) compared to the different flight phases described above. FIG. 2 illustrates the different lighting beams generated by the lighting system 1 according to the invention. It should be noted that the take-off and landing beams are here merged and referenced L / TO.
    The lighting system 1 makes it possible not only to reduce the number of equipment required but also to optimize its performance in order to improve the elements of the scene surrounding the aircraft visible to the pilot as a function of each phase of flight and increase the light range of the approach and landing beams.
    The lighting system 1 is able to create at least one light beam for each flight phase from taxiing (“taxi” in English), turning (“runway turn-off”), takeoff (“ take-off ”in English) and landing in English. Alternatively, the lighting system 1 is capable of creating all or part of these lighting light beams.
    The lighting system 1 comprises an optical acquisition device 2, at least one long-range projector 12a, 12b, 13a, 13b, 14a, 14b comprising a light source 3a, 3b, servo means 4, and a control means 5 for the light sources 3a, 3b and control means 4 and, when applicable, means for moving at least one light source 3a, 3b.
    By controlling the light sources 3a, 3b is meant the duration of ignition, the control of the high-speed scanning device and their synchronization.
    All the elements included in the lighting system 1 are arranged as close as possible to one another so as to avoid the drawbacks described in the introduction.
    The control means 5 and the servo means 4 make it possible to modify the extent and the direction of at least one light beam 6a, 6b as a function of the flight phases (approach, landing, taxiing and takeoff) so that the light beams produced correspond at least to the light beams produced by the lighting systems fitted to aircraft according to the state of the art.
    Different embodiments of the invention will now be described in connection with the generation of the beams illustrated in FIG. 2. These embodiments refer to two long-range searchlights, each arranged on one wing of the aircraft, in particular at level of their rootings. However, it is obvious that the number and arrangement of long-range projectors can be changed without departing from the scope of the invention and without showing inventive step. In particular, when installing on the ventral fairing of the aircraft, it is only possible to use a long-range searchlight.
    In a first embodiment illustrated by FIG. 3, the lighting system 1 comprises two long-range projectors 12a, 12b each comprising a high-speed scanning device 7a, 7b provided with at least two rotating reflecting surfaces whose axes of rotation are orthogonal. Each set of at least two reflecting surfaces is arranged so that the beam leaving the corresponding light source 3a, 3b is reflected successively on one then the other of the reflecting surfaces 7a, 7b in rotation. Each reflecting surface is directly connected to the axis of a motor so that the motor axis is included in the plane of the reflecting surface.
    Depending on the position of the reflecting surfaces, their angular velocities and the duration of ignition of the light source, it is possible to illuminate a point, a line, a curve. It is also possible to illuminate a surface by juxtaposing a set of lines that are close enough together so that the observer does not see any space between them. Combined with a speed of production lower than the duration of retinal persistence, it is thus possible to produce complex figures traversed by a single point.
    In a particular embodiment, the light source 3a, 3b is a laser type source.
    Laser-type light sources have the advantage of being able to generate a significantly higher luminance than other light sources (LED, Incandescence or Discharge). It is thus possible to collimate and channel the light flux emitted in an extremely fine and narrow solid angle, which makes it possible to increase its range.
    Laser-type light sources also do not emit lost light. As the scanning of the laser spot remains in the solid angle of the useful beam, the lost light is non-existent. This does not create parasitic backscatter outside the useful beam. This situation improves the contrast of the lit scene and avoids glare towards the pilot when particles or fog are present.
    In another particular embodiment, the light source 3a, 3b is obtained by combination of three monochromatic light sources of the laser type, red, green and blue. The light source thus obtained makes it possible to benefit from the characteristics of the laser sources while presenting a color resulting from the chromatic combination of the red, green and blue sources. It is thus possible to obtain a white color or any color of the light spectrum. Such a characteristic makes it possible to reproduce the white lighting light as recommended in aeronautical standards. Such a characteristic in combination with the ability to project patterns also makes it possible to project diagrams or writings on the ground. It is thus possible to project information intended for the track personnel, in particular warnings or positioning instructions (danger zone in front of the reactors, blind spots of the pilot, aircraft identification, communication with the authorities in the event of aggression of the occupants (ex. sos), etc ...).
    According to another embodiment illustrated by FIG. 4, each long-range light projector 13a, 13b of the lighting system 1 also comprises at least one centered optical system with variable focal length 8a, 8b whose focus is occupied by the source luminous 3a, 3b.
    The centered optical system 8a, 8b is provided with means for moving the long-range light source 3a, 3b so that the direction of the light beam can be offset around the axis of the centered optical system 8a, 8b. In other words, the light source 3a, 3b can be moved in a plane perpendicular to the direction of the axis of the centered optical system 8a, 8b. When the axis of the centered optical system 8a, 8b is not aligned with the light beam, the focal point of the light beam at the output of the centered optical system 8a, 8b is offset so that the beam is deflected.
    Furthermore, the focal length variation of the centered optical system 8a, 8b allows the beam to be shaped.
    The centered optical system 8a, 8b can also be provided with striated and prismatic glass 9a, 9b making it possible to generate the final lighting beam 6a, 6b. The prismatic zones allow the incident rays to be deflected. The striated areas allow the incident rays to be spread out. The prismatic and striated areas can be superimposed to spread and deflect the incident rays. A striated and prismatic glass allows to deflect, distribute and generate the light beam.
    Used in combination, the centered optical system 8a, 8b and the striated and prismatic glass 9a, 9b make it possible to generate several beams with different orientations from a single source. By providing several zones of the striated and prismatic ice 9 provided with different combinations of prisms and ridges, it is possible to allow the generation of different beams, each having a different offset and spread.
    The centered optical system 8a, 8b making it possible to choose the zone to be lit and its centering, it is then possible to selectively illuminate each zone of the striated and prismatic glass 9a, 9b so as to choose which beam is illuminated according to the beams provided on striated and prismatic ice. It is also possible to generate several beams by illuminating a larger area of the striated and prismatic ice 9a, 9b.
    Furthermore, the lighting system 1 may comprise several centered optical systems each associated with at least one striated and prismatic glass.
    In a particular embodiment, the light source 3a, 3b is a laser type source. In another particular embodiment, the light source 3a, 3b is obtained by combination of three monochromatic light sources of the laser type, red, green and blue. The light source thus obtained makes it possible to benefit from the characteristics of the laser sources while presenting a color resulting from the chromatic combination of the red, green and blue sources. It is thus possible to obtain a white color or any color of the light spectrum. Such a characteristic makes it possible to reproduce the white lighting light as recommended in aeronautical standards. Such a characteristic in combination with the ability to project patterns also makes it possible to project diagrams or writings on the ground. It is thus possible to project information intended for the track personnel, in particular warnings or positioning instructions (danger zone in front of the reactors, blind spots of the pilot, aircraft identification, communication with the authorities in the event of aggression of the occupants (ex. sos), etc ...).
    According to another embodiment illustrated in FIG. 5, each long-range light projector 14a, 14b of the lighting system 1 comprises an assembly 10a, 10b of at least two phosphors. Recall that a phosphor is a substance that absorbs light at a first wavelength to re-emit light at a second wavelength.
    The phosphors 10a, 10b are arranged so as to each cover a predefined direction of emission of a light beam so that each pointing direction is covered by the lighting of the corresponding phosphor.
    The ignition of one of the phosphors 10a, 10b is carried out either by the ignition of a corresponding illumination source, in particular a laser source at the absorption frequency of the phosphor. In a particular embodiment, the light source 3a, 3b of the laser type and the phosphors 10a, 10b are fixed with respect to each other. The slaving of beam projection and shaping optics allows the illumination of the predefined runway zones during the different approach, landing, taxiing and take-off at night phases.
    The lighting of one of the phosphors 10a, 10b can also be achieved by selective scanning of the phosphor via a light source 3a, 3b associated with a high speed scanning device 7a, 7b as illustrated by Figure 5. In the latter case, several phosphors can be illuminated by a single light source.
    In both cases, each of the phosphors 10a, 10b behaves like a secondary light source and is placed at the focus of a projection optic 11a, 11b.
    FIG. 6 illustrates the different stages of a control method according to the invention.
    In a first step 20, an image of the scene in front of the plane is acquired. We then carry out a pattern recognition in order to distinguish the various objects present, in particular the track, the signaling on the ground, and possible obstacles.
    In a second step 21, flight information is obtained from the aircraft data network in order to determine the current flight phase. This information includes speed, altitude and attitude angle. Other information can be taken into account such as the thrust, the reverse thrust state, the ground contact of the wheels, the position of the leading edges and flaps. Based on the information acquired and a predetermined model, the current flight phase is determined.
    In a third step 22, the at least one light beam to be switched on is determined, as well as their direction and spread as a function of the determined flight phase and of the objects recognized in front of the aircraft.
    To achieve this and for each lighting beam to be lit, the vertical angle, the horizontal angle and the pointing direction of the beam are determined by means of an image processing algorithm, the latter being derived from the integrated optical acquisition device, so that the beam illuminates a predefined area of space in front of the aircraft. Thus, for each type of light beam, the coordinates and the extent of the area to be illuminated are memorized. These values are then corrected according to flight data and recognized objects. In particular, the coordinates and the extent of the area to be illuminated are corrected as a function of the respective positions of the runway and the aircraft.
    Once the direction and spread of each light beam has been determined, during a fourth step 23, the instructions corresponding to the direction of the light sources 3a, 3b, the control means 4 and when this is determined are determined. applicable, means for moving at least one light source.
    The process is carried out in a loop as long as the aircraft is in one of the flight phases concerned.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Lighting system for an aircraft, characterized in that it comprises at least one optical acquisition device, at least one long-range projector (12a, 12b, 13a, 13b, 14a, 14b) each comprising at less a light source (3a, 3b), control means (4), and a control means (5) of the light sources (3a, 3b), according to the data received from the optical acquisition device and an aircraft data network so that the lighting system produces at least one light beam adaptively with respect to the flight and taxiing phases of the aircraft so as to illuminate at least one predefined area of the space around the aircraft.
    [2" id="c-fr-0002]
    2. System according to the preceding claim, wherein the long-range light projector (12a, 12b, 13a, 13b, 14a, 14b) is capable of illuminating a runway for aircraft at a distance of at least 300m.
    [3" id="c-fr-0003]
    3. System according to claim 1 or 2, in which the long-range projector (12a, 12b, 13a, 13b, 14a, 14b) comprises a high-speed scanning device (7a, 7b) provided with at least two surfaces rotating reflectors, the axes of rotation of which are orthogonal and arranged so that the beam leaving the light source (3) is reflected successively on one then the other of the reflecting surfaces.
    [4" id="c-fr-0004]
    4. The system of claim 1 or 2, wherein the long range projector (12a, 12b, 13a, 13b, 14a, 14b) comprises at least one centered optical system with variable focal length (8a, 8b) or at least one system centered fixed focal optic whose focal plane is occupied by a light source (3a, 3b), as well as means for moving the light source (3a, 3b) so that the direction of the light beam can be tilted relative to the axis of the optical system centered (8a, 8b) and / or moved perpendicular to the focal plane so that the opening of the beam can be enlarged.
    [5" id="c-fr-0005]
    5. The system as claimed in claim 4, in which the long-range projector (12a, 12b, 13a, 13b, 14a, 14b) comprises striated and prismatic glass (9a, 9b), disposed at the outlet of the centered optical system (8a, 8b) and making it possible to generate at least one lighting beam.
    [6" id="c-fr-0006]
    6. System according to any one of the preceding claims, in which the long-range projector (12a, 12b, 13a, 13b, 14a, 14b) comprises an assembly (10a, 10b) of at least two phosphors, each suitable for absorb the light emitted by a light source (3a, 3b) and re-emit white light.
    [7" id="c-fr-0007]
    7. System according to any one of the preceding claims, in which the light source (3a, 3b) is a laser type light source or a laser type light source obtained by combination of a monochromatic light source of color laser type. red, of a monochromatic light source of laser type of green color and of a monochromatic light source of laser type of blue color.
    [8" id="c-fr-0008]
    8. Method for controlling a lighting system according to any one of the preceding claims, characterized in that it comprises the following steps:
    we acquire an image of the scene in front of the plane with at least one optical acquisition device (2), we perform pattern recognition on the acquired image of the scene in order to distinguish the various objects present, in particular the runway, ground signaling, and possible obstacles, flight information is obtained from the aircraft data network, the current flight phase is determined based on the information acquired and a predetermined model, at least one determines a light beam to be switched on as well as their direction and spread as a function of the determined flight phase and of the objects recognized in front of the airplane, the directions for the direction of the light sources (3a, 3b) are determined, means for servo-control (4) and when applicable, means for moving at least one light source as a function of the lighting beams to be switched on as well as their directions and their spreads.
    [9" id="c-fr-0009]
    9. Method according to claim 8, in which the flight information comprises at least one value among the speed,
    5 altitude, attitude angle, thrust, thrust reversal state, contact with the wheels on the ground, position of leading edges and flaps.
    [10" id="c-fr-0010]
    10. Method according to any one of claims 8 or 9, in which to determine at least one light beam to be
    10 switch on as well as their direction and spread, for each lighting beam to be switched on, the vertical angle, the horizontal angle and the opening of the beam are determined according to predetermined values of the coordinates and of the extent of the area to be illuminated so that the beam illuminates a predefined area of the space around the aircraft, then the values determined are corrected as a function of the flight data comprising at least the respective positions of the runway and the aircraft.
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    CN105675532A|2016-04-01|2016-06-15|南京英田光学工程股份有限公司|Optical system of intermediate infrared laser radar|
    KR101899981B1|2016-12-02|2018-09-19|엘지전자 주식회사|Head Up Display for Vehicle|US10830408B1|2019-07-05|2020-11-10|Honeywell International Inc.|Lighting devices with variable beam patterns|
    EP3766785A1|2019-07-18|2021-01-20|Airbus Operations, S.L.U.|Lighting system for an aircraft|
    US11192494B2|2020-02-07|2021-12-07|Honeywell International Inc.|Systems and methods for search and landing light|
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    法律状态:
    2019-02-01| PLSC| Search report ready|Effective date: 20190201 |
    2019-04-10| PLFP| Fee payment|Year of fee payment: 3 |
    2020-06-23| PLFP| Fee payment|Year of fee payment: 4 |
    2021-04-23| CD| Change of name or company name|Owner name: SAFRAN ELECTRONICS & DEFENSE COCKPIT SOLUTIONS, FR Effective date: 20210319 |
    2021-06-23| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1757213|2017-07-28|
    FR1757213A|FR3069528B1|2017-07-28|2017-07-28|LIGHTING SYSTEM FOR AN AIRCRAFT|FR1757213A| FR3069528B1|2017-07-28|2017-07-28|LIGHTING SYSTEM FOR AN AIRCRAFT|
    US16/040,408| US20190032879A1|2017-07-28|2018-07-19|Lighting system for an aircraft|
    ES18185396T| ES2805074T3|2017-07-28|2018-07-25|Lighting system for an aircraft|
    EP18185396.1A| EP3434601B1|2017-07-28|2018-07-25|Lighting system for an aircraft|
    CN201810847544.XA| CN109323211A|2017-07-28|2018-07-27|Lighting system for aircraft|
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