FR3063488A1 - DEVICE FOR LIGHTING THE INTERIOR OF AN AIRCRAFT - Google Patents

Abstract

The invention proposes a lighting device (1) for the interior of an aircraft, comprising: - a lamp (10), comprising: ○ a source (11) of surface light emission, ○ a diffuser (13) , and ○ a guiding casing (12) of the light, - a control device (20) of the lamp (10), and - an articulated support (30) of the lamp, wherein the lamp (10) is in further adapted to emit a variable luminous flux between a minimum flux greater than or equal to 5,500 μm and a maximum flux greater than or equal to 18,000 μm, and the controller (20) is configured to allow selection of a luminous flux value emitted by the lamp from a finite set of discrete values of luminous flux.

Description

® FRENCH REPUBLIC

NATIONAL INSTITUTE OF INDUSTRIAL PROPERTY © Publication number: 3,063,488 (to be used only for reproduction orders) © National registration number: 17 51800

COURBEVOIE © IntCI ⁸ : B 64 F 5/10 (2017.01), F 21 V 21/26

A1 PATENT APPLICATION

(© Date of filing: 06.03.17. © Applicant (s): NEXEYA FRANCE Company by (© Priority: simplified actions - FR. @ Inventor (s): MAS SEBASTIEN. @) Date of public availability of the request: 07.09.18 Bulletin 18/36. (© List of documents cited in the report of preliminary research: Refer to end of present booklet (© References to other national documents (® Holder (s): NEXEYA FRANCE Joint-stock company related: simplified. ©) Extension request (s): © Agent (s): CABINET PLASSERAUD.

PA LIGHTING DEVICE FOR THE INTERIOR OF AN AIRCRAFT.

FR 3,063,488 - A1 (b /) The invention provides a lighting device (1) for the interior of an aircraft, comprising:

- a lamp (10), comprising:

O a source (11) of surface light emission,

O a diffuser (13), and

O a light guide housing (12),

- a control device (20) for the lamp (10), and

an articulated support (30) of the lamp, in which the lamp (10) is further adapted to emit a variable light flux between a minimum flux greater than or equal to 5500 Im and a maximum flux greater than or equal to 18000 Im, and the remote-controlled device (20) is configured to allow a selection of a light flux value emitted by the lamp from a finite set of discrete light flux values.

i

FIELD OF THE INVENTION

The invention relates to a lighting device for the interior of an aircraft, and to a lighting method with said device.

The invention is advantageously used in the context of the final assembly line of the aircraft.

STATE OF THE ART

In a final assembly line of an aircraft, operators must intervene in the aircraft whose fuselage is closed to carry out internal equipment integration operations, so an example is the mounting of seats.

Because the fuselage is closed and inside a building, this environment is very dark and needs to be lit to allow operators to work there.

The result to be achieved for lighting allowing comfortable working conditions is a color temperature illumination of 4000 ° K, and a luminance of the order of 7000 cd / m ² .

To illuminate the interior of the aircraft, operators sometimes use floor-standing lights that require the deployment, inside the aircraft, of equipment and cables that are very troublesome for operators. This solution therefore generates a loss of time and efficiency.

It is also known from document W02008081367, to simulate the ambient lighting of a fighter aircraft during a flight, to illuminate the environment around the aircraft by means of a set of lighting panels mounted on a dome-shaped structure, and to use a spotlight which is mounted on a support arm and which can be oriented towards the cockpit, in order to simulate the position of the sun.

However, this solution is not satisfactory since the objective is to simulate ambient natural lighting and not to illuminate the interior of the aircraft with sufficiently intense and correctly positioned light to allow operators to work. In fact, the support arm, because of its fixed length and its limited degrees of freedom, cannot be positioned precisely with respect to the aircraft. This can result in a lack of lighting of the areas of interest of the aircraft and of the large drop shadows which hamper the work of the operators.

DESCRIPTION OF THE INVENTION

The invention aims to overcome the shortcomings of the prior art, by proposing a lighting solution for the interior of the aircraft which is as close as possible to daylight and does not bring shadows on work areas.

In this regard, the subject of the invention is a device for lighting the interior of an aircraft, comprising:

- a lamp, comprising:

o a surface light emission source, o a diffuser, and o a housing guiding the light emitted by the source towards the diffuser,

- a lamp control device, and

- an articulated lamp support, adapted to allow positioning of the lamp outside the aircraft according to a determined position and orientation relative to a porthole or a window of the aircraft cockpit, in which the lamp is further adapted to emit a variable luminous flux between a minimum flux greater than or equal to 5500 Im and a maximum flux greater than or equal to 18000 Im, and the control device is configured to allow selection of a value of emitted luminous flux by the lamp among a finite set of discrete luminous flux values.

Advantageously, but optionally, the lighting device according to the invention can also comprise at least one of the following characteristics:

- the lamp may have an angle of emission of luminous flux greater than or equal to 65 °, preferably equal to 100 °.

- the source may have an emission surface greater than or equal to 500 cm ² ,

- the casing may include opaque walls extending from the light emission source to the diffuser, the internal faces of the casing walls being matt and white in color.

the light emission source may include a set of light emitting diodes or a continuous surface of organic light emitting diodes OLEDs.

the light emitted by the light source may have a color temperature between 3800 and 4200 K, preferably equal to 4000K, and a color rendering index greater than 70.

- The diffuser can be of microprismatic type.

- the articulated support can include:

o a suspension bracket to a raised floor, o an arm mounted to rotate relative to said bracket along an axis XX, and o a lamp support fork, mounted to rotate relative to the arm along an axis XX, and adapted for receive the lamp in pivot connection along an axis YY orthogonal to the axis XX.

the lighting device can comprise two lamps and an articulated support, and the arm of the articulated support comprises a first rectilinear portion, one end of which is mounted for rotation relative to the bracket, and a second portion comprising two auxiliary arms assembled in a V one end of which is assembled with a respective lamp support fork, and the other end of which is assembled with the first portion, the spacing of the auxiliary arms being adjusted according to the model of the aircraft.

The invention also relates to a method of lighting the interior of an aircraft, comprising the supply of a lighting device according to the above description outside the aircraft, and the positioning of the lamp relative to a porthole or window of the aircraft cockpit in an orientation normal to the surface of the porthole or window, and at a distance between 5 and 30 cm, preferably between 5 and 10 cm, between the window or window and the lamp diffuser.

The proposed lighting device, comprising a lamp and an articulated support, allows uniform lighting of the interior of an aircraft. On the one hand, the articulated support makes it possible to position the lamp precisely with respect to a porthole or a cockpit window of the aircraft to maximize the light flux transmitted inside and minimize the shadows cast. On the other hand, the surface character of the light source, as well as the diffuser make it possible to provide a diffusing and uniform lighting satisfactory for the work area.

Finally, the adjustable luminous flux of the lamp makes it possible to provide satisfactory light through the portholes which are covered with filters of variable characteristics. The different levels of light flux generated by the lamp make it possible to adapt to the various filters with which the windows are fitted, and to obtain a luminance inside the aircraft of the order of 7000 cd / m ² , allowing operators to work in good conditions.

DESCRIPTION OF THE FIGURES

Other characteristics, objects and advantages of the invention will emerge from the description which follows, which is purely illustrative and not limiting, and which should be read with reference to the appended drawings in which:

FIG. 1 represents an example of a lighting device according to an embodiment of the invention,

FIG. 2 is a top view of the lighting device in FIG. 1,

FIG. 3 represents a lamp of a lighting device,

FIG. 4 represents two examples of positioning of a lamp of a lighting device with respect respectively to a porthole and to a window of the cockpit of an airplane.

DETAILED DESCRIPTION OF AT LEAST ONE EMBODIMENT OF THE INVENTION

Referring to Figures 1 and 2, there is shown an example of lighting device 1, for lighting the interior of an aircraft, typically an aircraft, during manufacture, from the outside, through a porthole or window of the aircraft cockpit.

This lighting device comprises at least one lamp 10, a control device 20 for the lamp 10, and an articulated support 30 for the lamp.

Referring to Figure 3, the lamp 10 comprises a light source 11, adapted to emit light in the visible range. The light source 11 is areal to allow uniform lighting.

Preferably, the light source comprises a set of LEDs or light-emitting diodes distributed over a surface. Alternatively, the light source may include a continuous emissive surface formed by organic light emitting diode or OLED.

In all cases, the emission surface of the light source 11 is preferably greater than or equal to 500 cm ² , for example equal to 900 cm ² , that is to say a square surface with a side of 30 cm. The light emitted by the light source 11 has a color temperature between 3800 and 4200 K, and a color rendering index (CRI) greater than or equal to 70, preferably greater than or equal to 80.

In addition, the light source 11 has an angle of emission of light flux which is advantageously at least 65 °, preferably greater than or equal to 80 °, and even more advantageously equal to 100 °.

The lamp further comprises a diffuser 13, adapted to diffuse the light emitted by the light source 11 at a diffusion angle which is preferably at least 20 ° (angle added by the diffuser to the angle of emission of flux light source).

The diffuser 13 is preferably of microprismatic type. It can be in another embodiment of a microlens array. According to another variant, the diffuser can be a panel made of transparent material with one or two diffusing faces, for example frosted. According to yet another variant, the diffuser can be a panel made of a mass-diffusing material, for example opaline glass.

Finally, to channel the light from the light source 11 to the diffuser 13, the lamp comprises a guide casing 12, comprising opaque walls 120 extending from the light source 11 towards the diffuser 13. Advantageously, the walls 120 each have a matt white interior face, in order to reflect the light towards the diffuser in a homogeneous way. This can be achieved by means of a specific coating for the inside, or by using a mass-dyed material.

Advantageously, the walls 120 of the guide casing 12 include perforations 121 allowing the heat that can be generated by the light source 11 to be removed. In this case, the perforations preferably have a diameter of less than 3 mm, and are located outside of light flux transmission zones of the housing, in order to limit as much as possible the losses of light flux between the light source 11 and the diffuser 13.

The diffuser advantageously extends parallel to the emission surface of the light source.

The lamp is adapted to generate a variable luminous flux according to a plurality of distinct values. Advantageously, the light flux generated by the lamp is variable between a minimum value greater than or equal to 5500 Im, and a maximum value greater than or equal to 18000 Im, for example equal to approximately 24000 Im.

In addition, the lamp control device 20 is configured to allow the selection by an operator of a light flux value from a finite set of discrete light flux values, each value being determined according to a type of filter. optical present on a window or window of an aircraft, this in order to guarantee sufficient luminance inside the aircraft, whatever its model.

Thus according to an advantageous but nonlimiting example, the control device is configured to allow the selection of a light flux value from at least four discrete values, and preferably from four discrete values corresponding to four optical filters which are currently installed on aircraft windows or windows, for example:

- a first value equal to the minimum flux value, ie 5500 Im;

- a second value equal to 11300 Im;

- a third value equal to 15800 Im, and

- a fourth value equal to the maximum flux value, for example equal to 24000 Im.

This adjustable character of the light flux makes it possible to obtain, whatever the aircraft model (and therefore the model of the portholes, cockpit windows, and the filters which cover them), a luminance of 7000 cd / m ^{2 per} interior of the aircraft.

For example, the light flux generated by the lamp can be adjusted by modulating the supply voltage of the light source, for example LEDs or OLEDs (depending on the composition of the light source). The different light flux values then correspond to a set of discrete supply voltage values allowing the generation of the corresponding flux.

The lamp control device 20 can be a remote control device, suitable for communicating with the lamp by a wireless link (as shown diagrammatically in FIGS. 1 and 2) or by a wired link. As a variant, the lamp control device 20 can be integrated into the lamp 20. In all cases, the control device comprises means for acquiring (not shown) an instruction from an operator concerning the selection the value of the luminous flux, the means being known to the person skilled in the art (for example touch screen, cursor or selection button, etc.)

Returning to FIGS. 1 and 2, the articulated support 30 of the lamp is adapted to enable the lamp to be positioned in a precise position and orientation relative to a porthole or a window, by allowing the lamp to be moved and oriented according to three orthogonal axes.

According to a preferred embodiment, an example of which is shown in FIGS. 1 and 2, the articulated support 30 comprises a suspension bracket 31 which can be fixed on a raised technical floor, on which operators can stand to intervene on a aircraft being assembled. The bracket comprises in this respect a clamping system 310 which can receive an edge of the technical floor and the tightening of which makes it possible to pinch the floor and to maintain the bracket in a vertical position under the floor.

The articulated support 30 further comprises an arm 32 mounted on the bracket by one end, being movable in rotation relative to the bracket 31 around an axis XX which corresponds to the main direction of the bracket, and a fork 33 of lamp holder which is assembled to the arm 32 at its other end, in a rotary manner about an axis parallel to the axis XX.

The fork 33 receives the lamp in rotary connection relative to an axis Y-Y which is orthogonal to the axis X-X.

In a variant not shown, the articulated support 30 may comprise an arm mounted at one end in biocable ball joint connection on the raised floor, the lamp being mounted at the opposite end of the arm in biocable ball joint connection.

According to a particular example which is that shown in FIGS. 1 and 2, the lighting device can comprise two lamps 10, 10 ′ in order to illuminate for example by the two sides a cockpit by opposite windows, or two portholes of the same side of an airplane, the two lamps being mounted on the same articulated support 30.

In this case each lamp 10, 10 ′ pivots with respect to a respective fork 33, 33 ’with respect to a respective Y-Y, Y-Y’ axis which is always orthogonal to the X-X axis.

In addition in this case, the arm 32 advantageously comprises a first rectilinear portion 320, one end of which is mounted on the bracket, and a second portion 321 comprising two auxiliary arms 322, 322 'assembled in a V shape, of which one end (at the base of V) is assembled at the free end of the portion 320, and the other end is assembled with a fork 33, 33 'respectively. The first portion and the second portion are fixed relative to each other to allow rotation of the entire arm 32 relative to the suspension bracket 31.

The spacing between the auxiliary arms 322, 322 ’is advantageously adjusted as a function of the aircraft model to be lit.

Finally, in this case of an articulated support 30 common for two lamps, the control device 20 is advantageously also common in order to be able to control simultaneously and in an identical manner the luminous fluxes of the two lamps because the windows of the cockpit of the same aircraft are generally coated with the same optical filters.

With reference to FIG. 4, the lighting device 1 described above makes it possible to light the interior of an aircraft, by positioning a lamp relative to a porthole or a cockpit window in a normal orientation relative to the porthole or window surface (in the case of curvature of the porthole or window, it is positioned relative to the midpoint), and at a distance extending between the porthole or window and the diffuser 13 of between 5 and 30 cm, and preferably between 5 and 10 cm.

Once the lamp is positioned, the control device is used to select a light flux value from among all of the possible discrete values, in order to obtain sufficient luminance inside the aircraft to allow operators to work, namely around 7000 cd / m ² .

Claims (11)

1. Lighting device (1) of the interior of an aircraft, comprising: - a lamp (10), comprising: o a source (11) of surface light emission, o a diffuser (13), and o a guide housing (12) of the light emitted by the source towards the diffuser, - a control device (20) for the lamp (10), and - an articulated support (30) of the lamp, adapted to allow positioning of the lamp (10) outside the aircraft according to a determined position and orientation relative to a porthole or a window of the cockpit of the aircraft, in which the lamp (10) is further adapted to emit a variable luminous flux between a minimum flux greater than or equal to 5500 Im and a maximum flux greater than or equal to 18000 Im, and the control device (20) is configured to allow selection of a light flux value emitted by the lamp from a finite set of discrete light flux values. 2. A lighting device (1) according to claim 1, in which the lamp (10) has an angle of emission of luminous flux greater than or equal to 65 °, preferably equal to 100 °. 3. Lighting device (1) according to one of claims 1 or 2, in which the source (11) has an emission surface greater than or equal to 500 cm ² , 4. Lighting device (1) according to one of claims 1 or 2, wherein the casing (20) comprises opaque walls (120) extending from the light emission source to the diffuser (13), internal sides of the housing walls being matt and white in color. 5. Lighting device (1) according to one of the preceding claims, in which the light emission source (10) comprises a set of ίο light-emitting diodes or a continuous surface of organic light-emitting diodes OLEDs 6. Lighting device (1) according to one of the preceding claims, in which the light emitted by the light source (10) has a color temperature of between 3800 and 4200 K, preferably equal to 4000K, and an index color rendering greater than 70. 7. Lighting device according to one of the preceding claims, in which the diffuser is of microprismatic type. 8. Lighting device (1) according to one of the preceding claims, in which the articulated support (30) comprises: - a bracket (31) for suspension from a raised floor, an arm (32) rotatably mounted relative to said stem along an axis X-X, and - a lamp support fork (33), rotatably mounted relative to the arm along an X-X axis, and adapted to receive the lamp in pivot connection along a Y-Y axis orthogonal to the X-X axis. 9. A lighting device (1) according to claim 8, comprising two lamps (10, 10 d and an articulated support (30), in which the arm (32) of the articulated support (30) comprises a first portion (320) rectilinear, one end of which is mounted for rotation relative to the bracket, and a second portion (321) comprising two auxiliary arms (322) assembled in a V, one end of which is assembled to a respective lamp support fork, and the other end is assembled to the first portion (320), the spacing of the auxiliary arms (322) being adjusted according to the model of the aircraft. 10. A method of lighting the interior of an aircraft, comprising providing a lighting device according to one of the preceding claims outside the aircraft, and positioning the lamp relative to a porthole or window of the aircraft cockpit in an orientation normal to the surface of the porthole or window, and at a distance between 5 and 30 cm, preferably between 5 and 10 cm, between the porthole or the window and lamp diffuser. 11. The lighting method according to claim 10, further comprising the selection, as a function of the aircraft model, of a light flux value emitted by the lamp from among the set of discrete values, in order to reach a luminance inside the aircraft equal to 7000 cd / m ² . 1/2