Aircraft headlight comprising a glass plate provided with a light-scattering zone

Abstract

The invention relates to an aircraft headlight which comprises a housing provided with a glass plate (6) and a plurality of collimators which are arranged in the housing and are oriented toward the glass plate (6), wherein: the glass plate (6) comprises an inner face (6a) and an outer face (6b); the glass plate (6) is provided with at least one light-scattering zone (12) which faces at least one of the collimators; and a periodic pattern (26) which is provided with a rounded surface (26a) is formed on at least one of the inner face and outer face (6a, 6b) of the glass plate (6) in the light-scattering zone (12).

Description

[0001] DESCRIPTION

[0002] TITLE: Aircraft spotlight comprising a lens with a light-diffusion area

[0003] technical field

[0004] The invention relates technically to onboard lighting systems for aircraft.

[0005] In particular, the invention relates to an aircraft projector.

[0006] Previous techniques

[0007] Aircraft onboard lighting systems typically include several separate lighting devices that are activated according to the aircraft's flight or taxi phases.

[0008] An aircraft typically includes landing lights for illuminating the runway when the aircraft is on approach or during takeoff, and navigation lights. These lights may be located at the wing roots or under the wings when retractable, on the nose landing gear legs, or underneath the aircraft, particularly in the case of airplanes. These lights may also be fixed at the nose or retractable under the aircraft, especially in the case of helicopters.

[0009] The aircraft also includes lighting devices mounted on the aircraft's nose landing gear leg, or at the wing roots, or at the nose, or directly on the aircraft's fuselage, to illuminate the track on which the aircraft travels when moving on the ground, generally referred to by the Anglo-Saxons as "taxi lights", and additional lighting devices called in English "Runway Turn-Off lights" (RTO) which provide lateral lighting, also during taxiing.

[0010] Taxi lights and runway turn-off lights are activated during taxiing to illuminate the taxiways for exiting or entering a runway. During these phases, the lighting is characterized by a light distribution that allows for the identification of obstacles near the aircraft, primarily in front of the cockpit and wings. Initially equipped with incandescent lamps, these devices are now fitted with LEDs that produce focused beams of light in the vertical direction. In particular, the beams for landing and takeoff functions are typically characterized by a vertical and horizontal beam angle between 8 and 14 degrees, while taxi lights generally have beamwidths of approximately 45 degrees horizontally and 14 degrees vertically.

[0011] Description of the invention

[0012] The present invention aims to provide an aircraft projector whose emission of light beams is controlled.

[0013] Another objective of the invention is to provide an aircraft spotlight capable of illuminating in the near field and in particular up to below the aircraft.

[0014] An additional objective is to increase the number of lighting functions of an aircraft spotlight without increasing its size and mass.

[0015] The present invention relates to an aircraft projector comprising a housing equipped with a lens and a plurality of collimators arranged in the housing and oriented towards the lens, the lens comprising an inner face and an outer face.

[0016] The glass is provided with at least one light diffusion zone which is opposite at least one of the collimators, a periodic pattern which is provided with a rounded surface being formed on at least one of the inner and outer faces of the glass in said light diffusion zone.

[0017] The periodic pattern of said diffusion zone allows the light emitted by the collimator(s) opposite said diffusion zone to be refracted so as to diffuse this emitted light.

[0018] Thus, the said light diffusion zone allows a light beam emitted by the collimator(s) opposite the said diffusion zone to be spread out, and thus allows the distribution of light beams emitted by the aircraft projector to be modified locally compared to a projector equipped with a flat-faced lens.

[0019] By locally modifying the distribution of light beams, it is possible to increase the number of lighting functions of the aircraft projector without increasing its size and mass, in particular without increasing its depth.

[0020] The lens that supports the function allowing the modification of the light beam emission enables the use of standard collimators. It is therefore possible to modify the light beam emission simply by changing the lens, and thus without complicating the projector's structure or significantly altering its mass.

[0021] The term "a periodic pattern which has a rounded surface" means that the rounded surface of the periodic pattern is rounded by design, as opposed to a shape which is flat by design and is rounded as a result of a manufacturing defect, in particular a molding defect.

[0022] The aircraft spotlight can be retractable or fixed.

[0023] The retractable aircraft spotlight can be adjustable or non-adjustable.

[0024] Advantageously, said light diffusion zone is formed on the inner face of the glass.

[0025] Advantageously, the rounded surface of the periodic pattern of said diffusion zone is strictly convex or strictly concave.

[0026] According to a particular embodiment, the rounded surface of the periodic pattern of said diffusion zone has a constant radius of curvature.

[0027] Optionally, the radius of curvature of the rounded surface of the periodic pattern of said diffusion zone may be less than 3 millimeters, in particular less than or equal to 2 millimeters.

[0028] Optionally, the radius of curvature of the rounded surface of the periodic pattern of said diffusion zone may be greater than or equal to 0.2 millimeters.

[0029] The radius of curvature of the rounded surface of the periodic pattern may be greater than, equal to, or less than the period of the periodic pattern. Optionally, the periodic pattern of said diffusion zone is periodic in a first direction and uniform in a second direction that is perpendicular to the first direction.

[0030] Thus, the periodic pattern is invariant along the second direction and the diffusion generated by said diffusion zone takes place only along the first direction.

[0031] Optionally, said light diffusion zone is further configured to deflect the light at a non-zero angle.

[0032] The said light diffusion zone, which is further configured to deflect the light at a non-zero angle, can allow a beam of light from the projector to be directed downwards from the aircraft, i.e. towards the ground, for example to the vertical of the feet of a helicopter or to the lower limit of vision of an aircraft pilot to detect possible obstacles during landing or to better assess the distance to the ground.

[0033] The angle at which said diffusion area is configured to deflect the light can be strictly greater than 0 degrees and strictly less than 45 degrees.

[0034] According to a particular embodiment, the periodic pattern of said diffusion zone comprises the rounded surface and a flat surface which extends the rounded surface and which extends at least partly in the direction from the inner face to the outer face of the ice.

[0035] The periodic pattern of said diffusion zone may consist of the rounded surface and the flat surface which extends the rounded surface and which extends at least in part in the direction from the inner face to the outer face of the ice.

[0036] Optionally, the flat surface which extends at least partly in the direction from the inner face to the outer face of the ice may extend purely in the direction from the inner face to the outer face of the ice.

[0037] Optionally, the ice may include a plurality of diffusion zones, including at least one diffusion zone which is further configured to deflect light from a zero angle and at least one diffusion zone which is further configured to deflect light from a non-zero angle.

[0038] It is therefore possible to integrate into a projector, which is used in particular during the landing of the aircraft, a plurality of lighting functions, and in particular a "taxi" function or a "hover" function, otherwise known as a stationary flight function, while illuminating up to the lower limit of the pilot's vision.

[0039] Optionally, the ice may include a plurality of diffusion zones, including at least one diffusion zone which is further configured to deflect the light from a first non-zero angle and at least one diffusion zone which is further configured to deflect the light from a second non-zero angle different from the first non-zero angle.

[0040] Optionally, the ice may also include a prismatic area which is equipped with prisms.

[0041] Advantageously, each collimator includes a light source, a light input surface, a light output surface, and an intermediate collimation surface configured to collimate the light from the light input surface and direct it to the light output surface.

[0042] Optionally, the light entry surface of all or part of the collimators may be as described in FR 3 025 285.

[0043] Optionally, the light exit surface of all or part of the collimators may be as described in FR 3 049 266 or in application FR2307808 filed on behalf of the applicant of this application.

[0044] Optionally, the light exit surface of at least a portion of the collimators may include a periodic pattern which is provided with a rounded surface.

[0045] Advantageously, the light source for at least some of the collimators is an infrared light source, specifically a near-infrared light source configured to emit light with a wavelength between 700 nm and 1 pm. This makes the aircraft more easily detectable by aircraft equipped with infrared vision devices.

[0046] Optionally, the light source for part of the collimators is an infrared light source, while the light source for another part of the collimators is a visible light source.

[0047] Preferably, the infrared and visible light sources are independent so that it is possible to selectively activate infrared or visible lighting from the projector.

[0048] Advantageously, the glass includes polycarbonate.

[0049] Optionally, the plurality of collimators is arranged in collimator blocks, each block being equipped with a body which includes three lobes and which defines three collimators.

[0050] Optionally, the plurality of collimators is arranged at least in a first group of collimators arranged on a first flat face which is orthogonal to the direction from the inner face to the outer face of the ice, and in a second group of collimators arranged on a second flat surface which is inclined with respect to the first flat surface.

[0051] Advantageously, the projector glass includes a plurality of light diffusion zones so as to produce a plurality of beams among: a beam for aircraft takeoff, a first beam for aircraft landing, a second beam for aircraft landing which has a depth of field different from the depth of field of the first beam for landing, a first beam for aircraft taxiing, and a second beam for aircraft taxiing which has a beam angle, in particular horizontal, which is different from the beam angle, in particular horizontal, of the first beam for taxiing.

[0052] The present invention also relates to an aircraft, in particular a helicopter, comprising at least one projector as defined above.

[0053] The projector in question can be retractable.

[0054] The said projector may be orientable. When the aircraft is a helicopter, the said projector may be positioned under the helicopter or in the nose of the helicopter.

[0055] Brief description of the drawings

[0056] Other objects, features and advantages of the invention will become apparent from the following description, given solely by way of non-limiting example and made with reference to the accompanying drawings in which:

[0057] [Fig 1] illustrates a projector according to a first example of an embodiment of the invention;

[0058] [Fig 2] illustrates a collimator from figure 1 opposite an ice scattering area which is further configured to deflect the light by a non-zero angle;

[0059] [Fig 3] illustrates in perspective the diffusion zone of figure 2;

[0060] [Fig 4] illustrates in cross-section the diffusion zone of figure 2;

[0061] [Fig 5] illustrates in cross-section a diffusion zone of figure 1 which is further configured to deflect the light by a zero angle;

[0062] [Fig 6] illustrates different light beams emitted by the projector in Figure 1;

[0063] [Fig 7] illustrates a helicopter projector according to a second embodiment of the invention.

[0064] Detailed description

[0065] Figure 1 represents an aircraft projector 2 comprising a housing 4 fitted with a polycarbonate lens 6, a lens seal 8 to ensure the sealing of the housing 4 at the level of the lens 6, and a lens support 10 to fix the lens 6.

[0066] The ice 6 comprises an inner face 6a, an outer face 6b and a plurality of diffusion zones 12.

[0067] The interior of the housing 4 includes a base having a flat surface 4a which is orthogonal to the direction from the inner face 6a to the outer face 6b of the ice 6. Alternatively, the housing could have at least a first flat surface which is orthogonal to the direction from the inner face to the outer face of the ice, and at least a second flat surface which is inclined with respect to the first flat surface.

[0068] The projector 2 further includes a printed circuit board 14 disposed on the flat surface 4a of the housing 4 and a plurality of collimators 16 disposed in the housing 4 and oriented towards the glass 6. Alternatively, the projector could include at least a first printed circuit board disposed on the first flat surface of the housing, and at least a second printed circuit board disposed on the second flat surface of the housing.

[0069] The collimators 16 are here arranged in blocks 16a of collimators 16, each block 16a having a body which includes three lobes and which defines three collimators 16. Alternatively, the collimators could be arranged in at least a first group of collimators arranged on the first printed circuit board and in at least a second group of collimators arranged on the second printed circuit board.

[0070] As illustrated in Figure 2, each collimator 16 comprises a light source 18, a light entry surface 20, a light exit surface 22, and an intermediate collimation surface 24 suitable for collimating the light from the light entry surface 20 and directing it to the light exit surface 22. The light source 18 of each collimator 16 comprises, for example, a light-emitting diode connected to the printed circuit board 14. The light source 18 may be an infrared light source or a visible light source.

[0071] The light exit surface 22 of each collimator 16 is here flat. Alternatively, the light exit surface 22 of each collimator 16 could include a diffusion and / or refraction zone, or any other structure performing a light diffusion or deviation function.

[0072] Each light scattering zone 12 of the ice 6 is opposite at least one of the collimators 16 and includes a periodic pattern 26 which is here formed on the inner face 6a of the ice 6. With reference to Figures 3 to 5, the periodic pattern 26 of each scattering zone 12 includes a rounded surface 26a, in particular a convex rounded surface 26a.

[0073] The periodic pattern 26 of each diffusion zone 12 is periodic along a first direction of ice 6 and uniform along a second direction of ice 6, the second direction being perpendicular to the first direction. In other words, the diffusion zone 12 comprises several rows juxtaposed along the second direction of the pattern 26, which is periodic along the first direction.

[0074] Figures 3 and 4 represent a light scattering zone 12 which is also capable of deflecting light by a non-zero angle. For this, the periodic pattern 26 consists of the rounded surface 26a and a flat surface 26b extending from the rounded surface 26a, the flat surface 26b being oriented here along the first direction of the ice 6, that is to say that the normal to the flat surface 26b is oriented along the first direction.

[0075] The flat surface 26b of the periodic pattern 26 extends, in particular purely, in the direction from the inner face 6a to the outer face 6b of the ice 6 and in the second direction of the ice 6.

[0076] The flat surface 26b of each motif 26 considered extends on one side the rounded surface 26a of this motif 26 considered, and on the other side the rounded surface 26a of another motif 26 which is adjacent to the motif 26 considered.

[0077] A straight line passing through the endpoints of the rounded surface 26a of each pattern 26 considered forms an angle α with the flat outer surface 6b of the ice 6, which is strictly greater than 0 degrees and strictly less than 45 degrees, and which here forms an angle α of 19.5 degrees. These endpoints are taken along the first direction. The values ​​of the angle α, the radius of curvature of the rounded surface 26a, the period of the periodic pattern 26, and the refractive index of the material constituting the ice 6 allow us to determine the non-zero angle of light deviation. Figure 5 represents a light-difference zone 12 which is also capable of deflecting light by a zero angle. For this, the periodic pattern 26 consists solely of the rounded surface 26a, which has a constant radius of curvature, and here a constant curvature equal to the period of the periodic pattern 26.

[0078] Figure 6 represents the different lighting functions of an aircraft spotlight 2 which are implemented by means of collimators arranged in blocks and the different light diffusion zones 12 of the glass 6.

[0079] In particular, the projector 2 shown is capable of emitting a beam for the takeoff of aircraft 28a, a first beam for the landing of aircraft 28b, a second beam for the landing of aircraft 28c, a first beam for the taxiing of aircraft 28d, and a second beam for the taxiing of aircraft 28e.

[0080] To form the takeoff beam for aircraft 28a, the screen 6 includes a scattering zone with several rows of a pattern that is periodic about the first direction and has a radius of curvature strictly smaller than its period, for example, a radius of curvature at least 10% smaller than its period. The screen 6 further includes a scattering zone with one row of a pattern that is periodic about the first direction and has a radius of curvature strictly larger than its period, for example, a radius of curvature at least four times larger than its period. The screen 6 may also include a zone with prisms.

[0081] To form the first beam for the landing of aircraft 28b, ice 6 includes a diffusion zone with several rows of a pattern which is periodic along the first direction and which has a radius of curvature strictly greater than its period, for example a radius of curvature at least five times greater than its period.

[0082] To form the second beam for the landing of aircraft 28c, the ice 6 includes a diffusion zone with several rows of a pattern which is periodic along the first direction and which has a radius of curvature strictly greater than its period, for example a radius of curvature at least 30% greater than its period, a diffusion zone with several rows of a pattern which is periodic along the first direction and which has a radius of curvature less than its period, for example a radius of curvature at least 30% less than its period, and may further include a zone with prisms.

[0083] The second beam for the landing of aircraft 28c has a different depth of field than the first beam for the landing of aircraft 28b, and here a depth of field less than the depth of field of the first beam for the landing of aircraft 28b.

[0084] To form the first beam for taxiing aircraft 28d, the ice 6 includes a diffusion zone with several rows of a pattern which is periodic along the first direction and which has a radius of curvature strictly greater than its period, for example a radius of curvature at least twice as large as its period, and may further include a zone with prisms.

[0085] To form the second beam for taxiing aircraft 28e, ice 6 includes a diffusion zone with several rows of a pattern which is periodic along the first direction and which has a radius of curvature strictly less than its period, for example a radius of curvature at least 30% less than its period, and may further include a zone with prisms.

[0086] The second beam for taxiing aircraft 28e has a horizontal beam angle that is different from the horizontal beam angle of the first beam for taxiing aircraft 28d, and here a horizontal beam angle more than twice as large as the horizontal beam angle of the first beam for taxiing aircraft 28d.

[0087] Figure 7 represents a second example of the realization of a projector 2, which is here particularly adapted for a helicopter.

[0088] The projector 2 glass 6 here includes a flat area 30 in which the inner and outer surfaces of the glass are flat, as well as three diffusion areas 12a, 12b, 12c.

[0089] In this particular embodiment, a first diffusion zone 12a is capable of diffusing light in a horizontal direction. The first diffusion zone 12a is provided with a periodic pattern which is also capable of deflecting the light by a non-zero angle.

[0090] The second and third diffusion zones 12b, 12c are capable of diffusing light in a horizontal and vertical direction. The second and third diffusion zones 12b, 12c are each equipped with a periodic pattern which is also capable of deflecting the light by a non-zero angle; this periodic pattern is formed here with an angle α of 19.5 degrees in order to deflect the light vertically by 10 degrees, in particular to illuminate up to the vertical of the aircraft, for example up to the vertical of the aircraft's feet.

[0091] A first intensity diagram 32 illustrates the beam of a projector comprising a glass whose inner and outer surfaces are completely smooth.

[0092] A second intensity diagram 34 illustrates the beam of projector 2 including the ice 6. The beam of the second intensity diagram 34 is extended vertically and horizontally compared to the beam of the first intensity diagram 32.

[0093] On the second intensity diagram 34, references 12a, 12b, 12c and 30 were used to schematically represent the effects on the projector beam 2 of the first, second and third diffusion zones 12a, 12b, 12c and the planar zone 30 respectively.

Claims

DEMANDS 1. Aircraft spotlight (2) comprising a housing (4) equipped with a lens (6) and a plurality of collimators (16) disposed in the housing (4) and directed towards the lens (6), the lens (6) comprising an inner face (6a) and an outer face (6b), characterized in that the lens (6) is provided with at least one light-difference zone (12) which is opposite at least one of the collimators (16), a periodic pattern (26) which is provided with a rounded surface (26a) being formed on at least one of the inner and outer faces (6a, 6b) of the lens (6) in said light-difference zone (12), the lens (6) comprising a plurality of diffusion zones (12) of which at least one diffusion zone (12) is further configured to deflect the light by a first non-zero angle and at least one diffusion zone ( 12) which is further configured to deflect the light by a second non-zero angle and different from the first non-zero angle.

2. Aircraft projector (2) according to claim 1, wherein said light diffusion zone (12) is formed on the inner face (6a) of the glass (6).

3. Aircraft projector (2) according to claim 1 or 2, wherein the rounded surface (26a) of the periodic pattern (26) of said diffusion zone (12) is strictly convex or strictly concave.

4. Aircraft projector (2) according to any one of claims 1 to 3, wherein the periodic pattern (26) of said diffusion zone (12) is periodic along a first direction and is uniform along a second direction which is perpendicular to the first direction.

5. Aircraft projector (2) according to any one of claims 1 to 4, wherein said light diffusion zone (12) is further configured to deflect the light by a non-zero angle.

6. Aircraft spotlight (2) according to claim 5, wherein the periodic pattern (26) of said diffusion zone (12) comprises the rounded surface (26a) and a flat surface (26b) which extends the rounded surface (26a) and which extends at least partially into the direction from the inner face (6a) to the outer face (6b) of the ice (6).

7. Aircraft projector (2) according to any one of claims 1 to 6, wherein the lens (6) comprises a plurality of diffusion zones (12) of which at least one diffusion zone (12) is further configured to deflect the light by a zero angle and at least one diffusion zone (12) is further configured to deflect the light by a non-zero angle.

8. Aircraft spotlight (2) according to any one of claims 1 to 7, wherein each collimator (16) comprises a light source (18), a light inlet surface (20), a light outlet surface (22), and an intermediate collimation surface (24) configured to collimate the light from the light inlet surface (20) and direct it to the light outlet surface (22).

9. Aircraft projector (2) according to claim 8, wherein the light source (18) of at least a part of the collimators (16) is an infrared light source (18), in particular a near-infrared light source (18) which is configured to emit light radiation having a wavelength between 700 nm and 1 pm.

10. Aircraft, in particular helicopter, comprising at least one searchlight according to any one of claims 1 to 9.

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