Patent Description:
Rotorcraft are often equipped with exterior lights, such as landing lights and search lights, which are configured for emitting one or more light beams for enhancing the visibility of objects, such as obstacles and human beings, in the vicinity and/or in the flight path of the rotorcraft.

<CIT> discloses an exterior helicopter light unit with a dynamic output light intensity distribution includes a plurality of LEDs, and an optical system for shaping the output light intensity distribution from light emitted by the plurality of LEDs, wherein each of the plurality of LEDs contributes to the output light intensity distribution in an LED-specific output direction region, wherein at least a portion of the plurality of LEDs are individually dimmable, with a level of dimming for each of said portion of the plurality of LEDs in operation being set depending on a distance of the exterior helicopter light unit to ground in the respective LED-specific output direction region.

According to <CIT> a rotorcraft has on-board lighting equipment for lighting the surrounding environment. The lighting equipment comprises a plurality of headlights that are allocated to respective specific lighting functions in landing and in winching. The headlights are also operated to perform a searching lighting function. Control means determine which headlights are to be operated depending on a lighting function selected by an operator and depending on where the headlights are located on the rotorcraft.

The options of adjusting the distribution of light emitted by conventional exterior lights, however, are limited. In consequence, it may not be possible to adjust the distribution of the emitted light to the respective needs under a wide range of environmental and operational circumstances in a satisfactory manner.

Accordingly, it would be beneficial to provide improved rotorcraft lighting equipment, providing more flexibility for adjusting the distribution of the light emitted by the rotorcraft lighting equipment.

According to an exemplary embodiment of the invention, rotorcraft lighting equipment comprises a plurality of lighting devices, which are configured to be mounted to an exterior of a rotorcraft, each of the lighting devices comprising a plurality of individually controllable lighting modules, which are configured for emitting light into different spatial directions, allowing to generate different light distributions of the light emitted by the plurality of lighting modules. The rotorcraft lighting equipment further comprises a lighting control device, which is configured for individually controlling the operation of the pluralities of lighting modules of the plurality of lighting devices, depending on the respective spatial directions, for generating a desired light distribution, which is one of the different light distributions, of the light emitted by the pluralities of lighting modules.

Exemplary embodiments of the invention further include a rotorcraft, in particular a helicopter and/or a drone, comprising rotorcraft lighting equipment according to an exemplary embodiment of the invention.

Exemplary embodiments of the invention also include a method of illuminating an environment of a rotorcraft via a rotorcraft lighting equipment having a plurality of lighting devices, mounted to different positions of an exterior of the rotorcraft, with each of the lighting devices having a plurality of individually controllable lighting modules arranged for emitting light into different spatial directions, allowing to generate different light distributions of the light emitted by the pluralities of lighting modules of the plurality of lighting devices, wherein the method comprises: individually controlling, by a lighting control device, the pluralities of lighting modules of the plurality of lighting devices, depending on the respective spatial directions, for generating a desired light distribution, which is one of the different light distributions, in the environment of the rotorcraft.

Rotorcraft lighting equipment and methods of operating rotorcraft lighting equipment according to exemplary embodiments of the invention allow individually and continuously adjusting the distribution of light, emitted by the rotorcraft lighting equipment, to the current needs. Rotorcraft lighting equipment and methods of operating rotorcraft lighting equipment according to exemplary embodiments of the invention in particular allow for simultaneously illuminating different objects independently of each other. As a result, the distribution of light, emitted by the rotorcraft lighting equipment, may be optimized to the current operational condition and environment of the rotorcraft. The desired light distribution may comprise one or more illumination components. In particular, the desired light distribution may comprise at least one of a landing zone illumination component, a search area illumination component, a winch operation area illumination component, and an obstacle illumination component. The desired light distribution may comprise any subset or all of the landing zone illumination component, the search area illumination component, the winch operation area illumination component, and the obstacle illumination component.

According to an embodiment of the invention, lighting devices of the rotorcraft lighting equipment are configured to be mounted to different positions / locations of the exterior of the rotorcraft. This may allow the lighting devices to emit light in widely different directions from the rotorcraft. As a result, an area covering a large angular range surrounding the rotorcraft may be illuminated by the lighting devices. The rotorcraft may in particular be configured for selectively illuminating areas located in front of, behind, laterally from and/or below the rotorcraft.

According to an embodiment, each of the lighting devices is configured for emitting light with an intensity of at least <NUM> kcd, in particular with an intensity of at least <NUM> kcd. Lighting devices configured for emitting light with intensities of at least <NUM> kcd, in particular with intensities of at least <NUM> kcd, may provide for an effective illumination of the environment, in particular for detecting target objects in a dark environment.

According to an embodiment of the invention, each of the lighting modules comprises a plurality of lighting elements configured for emitting light into different spatial directions. Each of the plurality of lighting elements may be individually controllable by the lighting control device, and the lighting control device may be configured for individually controlling the operation of each of the plurality of lighting elements. Controlling the lighting elements may include individually switching the lighting elements on and off. Controlling the lighting elements may also include individually dimming the lighting elements, i.e. individually adjusting the amount (brightness) of light emitted by each of the lighting elements. The capability of individually controlling a plurality of lighting elements, provided in each of the lighting modules, increases the flexibility of adjusting the distribution of light, emitted by the rotorcraft lighting equipment, even further. The multi-layered approach of the rotorcraft lighting equipment having a plurality of lighting devices, which in turn have light modules, which in turn have lighting elements, may provide for a beneficial compromise between mechanical complexity, control complexity, and spatial resolution of the rotorcraft lighting equipment as a whole.

According to an embodiment, each of the plurality of lighting elements comprises at least one light source, in particular at least one LED. LEDs provide reliable light sources, having a high efficiency at comparatively low cost.

Each of the plurality of lighting elements may comprise exactly one light source. Each of the plurality of lighting elements may also comprise multiple light sources for increasing the amount of light which can be emitted by the respective lighting element. The light sources may be configured for emitting white light, in particular white light having a color temperature of at least <NUM>, more particularly white light having a color temperature of at least <NUM>, and/or colored light, in particular yellow and/or orange light. The light sources further may be configured for emitting infrared light.

According to an embodiment, each of the lighting modules comprises an array of at least 30x30, in particular 32x32 or 64x64 lighting elements, respectively. Each of the lighting modules may comprise an array of between 30x30 and 200x200 lighting elements, in particular an array of between 30x30 and 100x100 lighting elements. Providing an array of at least 30x30 lighting elements in each of the lighting modules provides a large amount of flexibility for adjusting the distribution of light, emitted by the rotorcraft lighting equipment, to the current needs.

According to an embodiment, each of the plurality of lighting elements comprises at least one optical element, associated with the light source of the lighting element in question and configured for directing and/or focusing the light emitted by the respective associated light source. The at least one optical element may comprise one or more lenses and/or one or more reflectors and/or one or more shutters. The at least one optical element may in particular include a collimating lens and/or a collimating reflector. Providing optical elements, respectively associated with one of the light sources, allows for adjusting and optimizing the distribution of light, emitted by the lighting elements; it allows in particular for forming a plurality of focused light beams, emitted by the plurality of lighting elements.

According to an embodiment, the plurality of lighting devices are configured to be mounted to the exterior of the rotorcraft in fixed positions and/or orientations, and the lighting modules are configured to remain stationary within the respective lighting devices. In such a configuration, the lighting modules of the respective lighting devices are configured to emit light into preset different spatial directions. The lighting elements may also be stationary within the respective lighting modules and may be configured for emitting the light in different spatial directions, respectively.

Such a rotorcraft lighting equipment does not comprise movable mechanical parts that need to be moved for adjusting the distribution of light to the current needs. Avoiding the need for mechanically movable parts may enhance the operational reliability of the rotorcraft lighting equipment and may reduce the need for repair and maintenance.

According to an embodiment, each of the lighting modules is configured for emitting light into a predefined spatial sector, in particular into a spatial cone having an opening angle of between <NUM>° and <NUM>°, further in particular between <NUM>° and <NUM>°, yet further in particular <NUM>°.

According to an embodiment, the lighting modules of each lighting device are arranged so that the predefined spatial sectors of adjacent lighting modules seam-lessly abut against each other, so that there are no unlit areas between adjacent illuminated areas. Such a rotorcraft lighting equipment may allow for generating a continuous illuminated area, which does not comprise any unlit dark gaps.

According to an embodiment, the lighting modules of each lighting device are arranged so that the predefined spatial sectors of adjacent lighting modules at least partially overlap with each other. The extension of overlap may include <NUM> % to <NUM> %, in particular <NUM> % to <NUM> %, of the respectively adjacent illuminated areas.

According to an embodiment, the lighting modules of each lighting device are arranged on a common mounting structure, in particular on a curved surface of the common mounting structure. The curved surface may in particular be a spherical or ellipsoidal surface. Arranging the lighting modules of each lighting device on a curved surface, such as a spherical or ellipsoidal surface, may cause the lighting modules to emit light in inherently different spatial directions, thereby covering a large spatial area, in particular a spatial area covering a large angle, with the light emitted by the plurality of lighting modules.

According to an embodiment, each lighting device comprises more than <NUM> lighting modules. Each lighting device may for example comprise <NUM> lighting modules. The <NUM> lighting modules may be arranged in a 6x6 matrix configuration or in a closed-packed circle configuration. A <NUM>×<NUM> matrix configuration and a closed-packed circle configuration allow for efficiently arranging <NUM> lighting modules with a comparatively small top area, resulting in a compact lighting device.

According to an embodiment, at least one of the lighting devices comprises another functional device, such as a camera or a laser-light source, which is arranged among the lighting modules. The other functional device may in particular be arranged in a center of the configuration of lighting modules. Adding another functional device, such as a camera or a laser-light source, adds additional functionality to the at least one lighting device. This may enhance the usefulness of the rotorcraft lighting equipment.

According to an embodiment, the plurality of lighting devices comprise at least two of the following lighting devices: a nose lighting device configured to be mounted to a nose (central front portion) of the rotorcraft, in particular to a region below the cockpit of the rotorcraft; a left front lighting device configured to be mounted to a left front portion of the fuselage of the rotorcraft; a right front lighting device configured to be mounted to a right front portion of the fuselage of the rotorcraft; a left rear lighting device configured to be mounted to a left rear portion of the fuselage of the rotorcraft; a right rear lighting device configured to be mounted to a right rear portion of the fuselage of the rotorcraft; and a belly lighting device configured to be mounted to an underside of the fuselage and/or to a landing gear of the rotorcraft. The plurality of lighting devices may comprise any subset or all of the nose lighting device, the left front lighting device, the right front lighting device, the left rear lighting device, the right rear lighting device, and the belly lighting device.

Rotorcraft lighting equipment comprising at least two of these lighting devices allows for illuminating different areas located around the rotorcraft by selectively operating the lighting modules of said lighting devices. The light distribution, which can be emitted by a combination of at least two of the above mentioned lighting devices, may in particular cover spatial areas extending in different directions from the rotorcraft.

According to an embodiment, a rotorcraft according to an exemplary embodiment of the invention further comprises a controllable winch, including a hooking device which may be lowered from the rotorcraft to pick up persons or objects being hooked to the hooking device. The rotorcraft may further comprise a winch control system, which is configured for controlling the operation of the winch.

In such a rotorcraft comprising a winch and a winch control system, the lighting control device may comprises a first control input associated with the winch and configured for allowing crew members, controlling the winch, to input control commands to the lighting control device for adjusting the distribution of light, emitted by the rotorcraft lighting equipment, in correspondence with the operation of the winch. Alternatively or additionally, the lighting control device may be coupled with the winch control system for allowing the winch control system to control the distribution of light, emitted by the rotorcraft lighting equipment, in correspondence with the operation of the winch.

According to an embodiment, the lighting control device is connected with a pilot input device, allowing a pilot, or another cockpit crew member of the rotorcraft, to input control commands to the lighting control device for adjusting the distribution of light, emitted by the rotorcraft lighting equipment, in order to allow for a safe operation of the rotorcraft.

According to an embodiment, the rotorcraft further comprises an automated anti-collision device, and the lighting control device is connected with the anti-collision device, allowing the anti-collision device to input control commands to the lighting control device for automatically adjusting the distribution of light, emitted by the rotorcraft lighting equipment, based on information provided by the anti-collision device. Such a configuration may for example allow for automatically illuminating potential obstacles, detected by the anti-collision device. This may enhance the safety of operating the rotorcraft, as potential obstacles may be illuminated and thereby made visible to the pilot at an early stage of approaching said potential obstacles.

According to an embodiment, the winch crew, the winch control system, the cockpit crew, in particular the pilot, and the anti-collision device may control the distribution of light emitted by the lighting equipment independently of each other. In consequence, the distribution of light may be simultaneously adjusted to different needs. According to an embodiment of the invention, the illumination of obstacles, for example, may not be affected by adjusting the light distribution generated for illuminating the operational area of the winch, and the light distribution generated for illuminating the operational area of the winch may not be affected when obstacles are identified and illuminated by adjusting the light distribution generated by the rotorcraft lighting equipment. As a result, the operational safety of the rotorcraft may be enhanced even further.

According to an embodiment, the method of illuminating an environment of a rotorcraft via rotorcraft lighting equipment comprises determining an illumination pattern for the current environment of the rotorcraft; mapping the illumination pattern to the different spatial directions of the plurality of lighting modules of the plurality of lighting devices; and individually controlling the plurality of lighting modules of the plurality of lighting devices on the basis of said mapping, in order to provide an optimized illumination of the current environment of the rotorcraft. These steps may be repeated, in particular periodically repeated, during the operation of the rotorcraft for adjusting the illumination of the environment of the rotorcraft to changing environmental conditions.

Embodiments of the invention are described in greater detail below with reference to the Figures, wherein:.

The helicopter <NUM> comprises a fuselage <NUM>, a main rotor <NUM> and a tail rotor <NUM>. Although not explicitly shown in the Figures, the helicopter <NUM> may alternatively comprise two counter-rotating main rotors <NUM> and no tail rotor <NUM>.

The helicopter <NUM> further comprises a cockpit <NUM> and a landing gear <NUM>. The landing gear <NUM> may include wheels <NUM> and/or skids <NUM>.

The helicopter <NUM> also comprises a winch <NUM> including a movable hooking device <NUM>, which may be lowered from the helicopter <NUM> for picking up persons <NUM> and/or objects <NUM>, and a winch control system <NUM>, which is configured for controlling the movement of the hooking device <NUM>.

Rotorcraft lighting equipment 2a-2d, <NUM> according to an exemplary embodiment of the invention comprises a plurality of lighting devices 2a-2d mounted to the helicopter <NUM>. In the embodiment depicted in <FIG>, the lighting devices 2a-2d are mounted to the fuselage <NUM> of the helicopter <NUM>.

The lighting devices 2a-2d are in particular mounted to portions of the fuselage <NUM> below the cockpit <NUM> of the helicopter <NUM> for conveniently illuminating regions <NUM> below the helicopter <NUM>.

The lighting devices 2a-2d in particular include a nose lighting device 2a, configured to be mounted to a central front portion ("nose") <NUM> of the fuselage <NUM> of the helicopter <NUM>; a left front lighting device 2b, configured to be mounted to a left front portion of the fuselage <NUM> of the helicopter <NUM>; a right front lighting device (not visible in <FIG>), configured to be mounted to a right front portion of the fuselage <NUM> of the helicopter <NUM>; a left rear lighting device 2c, configured to be mounted to a left rear portion of the fuselage <NUM> of the helicopter <NUM>; a right rear lighting device (not visible in <FIG>), configured to be mounted to a right rear portion of the fuselage <NUM> of the helicopter <NUM>, and a belly lighting device 2d, configured to be mounted to an underside of the fuselage <NUM> and/or to the landing gear <NUM> of the helicopter <NUM>.

Each lighting device 2a-2d comprises a plurality of lighting modules <NUM>, which are configured for emitting light in different spatial directions. The structure of the lighting modules <NUM> will be discussed in more detail further below referring to <FIG>.

The rotorcraft lighting equipment 2a-2d, <NUM> further comprises a lighting control device <NUM>, which is configured for individually controlling the operation of the plurality of lighting devices 2a-2d, in order to generate a desired light distribution of the light emitted by the plurality of lighting devices 2a-2d.

A pilot input device <NUM>, an anti-collision input device <NUM>, and a winch operator input device <NUM> are coupled to the lighting control device <NUM> and allow for inputting commands into the lighting control device <NUM>.

Different light distributions may be generated by appropriately controlling the operation of the plurality of lighting devices 2a-2d. As a result, different lighting functionalities may be realized by the rotorcraft lighting equipment 2a-2d, <NUM>. For example, the plurality of lighting devices 2a-2d may be controlled such that the rotorcraft lighting equipment 2a-2d, <NUM> operates as a helicopter landing light, illuminating a dedicated landing area. Additionally or alternatively, the lighting devices 2a-2d may be controlled such that the rotorcraft lighting equipment 2a-2d, <NUM> provides the functionality of a search light and/or of a winch light. Rotorcraft lighting equipment 2a-2d, <NUM> according to exemplary embodiments of the invention in particular may be operated to provide different types of lighting simultaneously and independently of each other.

The direction of one or more light beams, emitted by the rotorcraft lighting equipment 2a-2d, <NUM>, may be modified without moving the lighting devices 2a-2d with respect to the fuselage <NUM> of the helicopter <NUM>. In consequence, the rotorcraft lighting equipment 2a-2d, <NUM> according to exemplary embodiments of the invention may be employed as a landing light and/or as a search light and/or as a winch light, tracking a desired target object <NUM>, <NUM>, without employing mechanically movable parts. Avoiding the need for mechanically movable parts may enhance the operational reliability of the rotorcraft lighting equipment 2a-2d, <NUM> and reduce the need for repair and maintenance.

Each of the lighting devices 2a-2d may be configured for emitting light with an intensity of at least <NUM> kcd, in particular with an intensity of at least <NUM> kcd. Lighting devices 2a-2d configured for emitting light with intensities of least <NUM> kcd, may provide for an effective illumination of the environment, in particular for detecting target objects in a dark environment.

<FIG> depicts a schematic view of a lighting device 2a, as may be used in rotorcraft lighting equipment according to an exemplary embodiment of the invention.

The lighting device 2a comprises a plurality of lighting modules <NUM>, arranged in a six by six (6x6) rectangular, in particular quadratic, configuration.

The arrangement of the lighting modules <NUM> depicted in <FIG> is only exemplary, and a lighting device 2a according to an exemplary embodiment of the invention may comprise more or less than <NUM>×<NUM> (<NUM>) lighting modules <NUM>. The lighting modules <NUM> also may be arranged in different configurations than the rectangular configuration depicted in <FIG>.

<FIG>, for example, depicts an alternative configuration, in which <NUM> lighting modules <NUM> are arranged in a closed-packed circle configuration, resulting in a basically circular outer contour of the lighting device 2a'. Of course, more or less than <NUM> lighting modules <NUM> may be arranged in a closed-packed circle configuration as well.

In the closed-packed circle configuration depicted in <FIG>, the <NUM> lighting modules <NUM> are arranged around a central module <NUM>, which is arranged at the center of the circular configuration. The central module <NUM> may be an additional (37th) lighting module <NUM>, or it may be an alternative functional device <NUM>, such as a camera or a laser-light source, adding additional functionality to the lighting device 2a'.

In alternative configurations, which are not explicitly shown in the Figures, any of the lighting modules <NUM> may be replaced by such an alternative functional device <NUM>, or at least one of the lighting modules <NUM> may additionally include such an alternative functional device <NUM> for adding additional functionality to the lighting device <NUM>.

The lighting modules <NUM> are configured for emitting light into different spatial directions. The distribution of light, emitted by each lighting device, may be adjusted by selectively switching the lighting modules <NUM> on and/or off.

In order to cause the lighting modules <NUM> to emit light in different spatial directions, the lighting modules <NUM> may be arranged on a curved surface <NUM> of a mounting structure <NUM> of the lighting device 2a', resulting in different spatial orientations of the lighting modules <NUM>. It is also possible that the lighting modules <NUM> are arranged on a substantially plane mounting structure and that the different spatial directions are achieved via inclining light sources and/or via directing light into the different spatial directions via according optical systems.

<FIG> schematically depicts a cross-sectional view through a lighting device 2a", comprising a mounting structure <NUM> having a curved outer peripheral surface <NUM>. The lighting modules <NUM> are arranged on said curved surface <NUM>. The curved surface <NUM> may be a part of a sphere, such as a hemisphere, allowing the lighting device 2a" to emit light in an angular range of <NUM>° in a first plane, and to emit light in an angular range of <NUM>° in a second plane, which is oriented orthogonally to the first plane.

The curved surface <NUM>, however, does not need to be a spherically shaped surface <NUM>. The curved surface <NUM> may, for example, have the shape of a portion of an ellipsoid, i.e. it may be elliptical in cross-section. The curved surface <NUM> may further have any other convex or concave shape which is suitable for generating desired different spatial directions for the light, emitted by the lighting modules <NUM>.

Each of the lighting modules <NUM> may be configured for emitting light into a predefined spatial sector <NUM>, in particular into a spatial cone <NUM> having an opening angle γ of between <NUM>° and <NUM>°, further in particular between <NUM>° and <NUM>°, yet further in particular <NUM>°.

A lighting device 2a, 2a' comprising <NUM> lighting modules <NUM>, as depicted in <FIG>, wherein each of the lighting modules <NUM> is configured for emitting light into a spatial cone <NUM> having an opening angle of <NUM>°, allows for emitting light in an overall light cone having an opening angle of <NUM>°.

<FIG> shows a plan view of a lighting module <NUM>, as may be used in rotorcraft lighting equipment according to an exemplary embodiment of the invention. The lighting module <NUM> depicted in <FIG> includes a semiconductor chip <NUM> comprising a plurality of lighting elements <NUM>. The semiconductor chip <NUM> has a rectangular shape, and the plurality of lighting elements <NUM> are arranged in a rectangular configuration, in particular in a quadratic configuration, having a side length L of <NUM> to <NUM>, in particular a side length L of <NUM>.

In the exemplary embodiment depicted in <FIG>, the lighting module <NUM> comprises <NUM> x <NUM> (=<NUM>) lighting elements <NUM>. The individual lighting elements <NUM> are configured for emitting light in different directions, and the individual lighting elements <NUM> may be operated independently from each other. As a result, the distribution of light, emitted by each of the lighting modules <NUM>, may be adjusted by selectively operating the individual lighting elements <NUM>.

Selectively operating the individual lighting elements <NUM> may include switching the lighting elements <NUM> individually on and off. Selectively operating the individual lighting elements <NUM> may also include individually dimming the lighting elements <NUM>, i.e. individually adjusting the amount (brightness) of light emitted by each of the lighting elements <NUM>.

Dimming the lighting elements <NUM> may include adjusting the brightness of the light emitted by each of the lighting elements <NUM> on a continuous scale. It may also include switching the brightness of the light, emitted by each of the lighting elements <NUM>, between a plurality of discrete operational modes, wherein the brightness of the light emitted by each of the lighting elements <NUM> is different in each of said operational modes.

<FIG> depicts a cross-sectional side view through a lighting element <NUM>, as may be used in rotorcraft lighting equipment according to an exemplary embodiment of the invention.

The lighting element <NUM> comprises at least one light source <NUM>. The at least one light source <NUM> may in particular be at least one LED. In particular, a plurality of LEDs may be formed on a common substrate <NUM>. In the embodiment depicted in <FIG>, the lighting element <NUM> comprises three light sources <NUM>, formed on a common substrate or circuit board <NUM>.

The lighting element <NUM> further comprises an optical element <NUM>, in particular a lens <NUM>, which is configured for directing and focusing the light emitted by the light sources <NUM> and forming a light beam <NUM> emitted by the lighting element <NUM>.

Although only a lens <NUM> is shown in <FIG>, the lighting element <NUM> may further comprise a reflector and/or a shutter in addition or alternatively to the lens <NUM>. The optical element <NUM> may in particular be a collimating optical element <NUM>, such as a collimating lens and/or a collimating reflector.

The lighting element <NUM> also comprises an at least partially light transmissive cover <NUM>, covering and protecting the light source(s) <NUM> and the optical element <NUM>.

In the following, the principles of operating the rotorcraft lighting equipment 2a-2d, 2a', 2a", <NUM> according to an exemplary embodiment of the invention are explained with reference to <FIG>.

<FIG> depicts a schematic top view of a region below the helicopter <NUM>; the helicopter <NUM> itself is not shown in <FIG>.

The area <NUM> marks the maximum field of view of the cockpit crew <NUM> of the helicopter <NUM>. The area <NUM> indicates the maximum illuminable area <NUM> below the helicopter <NUM>, i.e. the maximum extent of the area that may be illuminated by operating the rotorcraft lighting equipment 2a-2d, 2a', 2a", <NUM>.

Areas 32a-32f are sub-areas 32a-32f of the illuminable area <NUM>, wherein each of said sub-areas 32a-32f is illuminable by one of the lighting devices of the rotorcraft lighting equipment, respectively.

The sub-areas 32a-32f abut against each other, constituting a continuous, i.e. seamless, illuminable area <NUM> below the helicopter <NUM>. Optionally, adjacent sub-areas 32a-32f may at least partially overlap with each other. Adjacent sub-areas 32a-32f may overlap over a portion of up to <NUM> %, in particular over a portion of up to <NUM> %, of the adjacent sub-areas 32a-32f.

An electric power line <NUM> representing a potential obstacle <NUM> is present in the illuminable area <NUM> below the helicopter <NUM>. In particular, when the helicopter <NUM> is flying at low heights and/or is approaching the ground <NUM> for landing, obstacles <NUM> such as electric power lines <NUM> need to be recognized by the cockpit crew <NUM>, in particular the pilot <NUM>, of the helicopter <NUM>, in order to avoid a collision of the helicopter <NUM> with such an obstacle <NUM>.

It is desirable to illuminate the obstacle <NUM>, in order to be recognized by the cockpit crew <NUM> of the helicopter <NUM>, even under adverse visibility conditions, in particular during the night, or when the helicopter is flying through fog, rain, etc..

In the example depicted in <FIG>, the lighting elements <NUM> of the rotorcraft lighting equipment 2a-2d, 2a', 2a", <NUM> are controlled for illuminating the power line <NUM>, i.e. an area <NUM> surrounding the power line <NUM>.

The rotorcraft lighting equipment 2a-2d, 2a', 2a", <NUM> may be controlled manually by the cockpit crew <NUM> by inputting control commands into the lighting control device <NUM> via the pilot input device <NUM> provided in the cockpit <NUM> (cf.

The rotorcraft lighting equipment 2a-2d, 2a', 2a", <NUM>, for example, may be operated as a landing light or as a manual search light, wherein the direction, the width and/ or the intensity of the light beam, emitted by the rotorcraft lighting equipment 2a-2d, 2a', 2a", <NUM>, are controlled manually by the cockpit crew <NUM> of the helicopter <NUM>, in particular by the pilot <NUM>, via the pilot input device <NUM>.

Additionally or alternatively, the rotorcraft lighting equipment 2a-2d, 2a', 2a", <NUM> may be controlled by an automated anti-collision device <NUM>, which is configured for detecting potential obstacles <NUM> in the flight path of the helicopter <NUM> and providing input to the lighting control device <NUM> via the anti-collision input device <NUM> for illuminating the detected potential obstacles <NUM>.

In the example depicted in <FIG>, the lighting elements <NUM> of the rotorcraft lighting equipment 2a-2d, 2a', 2a", <NUM> are further controlled to additionally illuminate an operational area <NUM> of the the winch <NUM>, i.e. an area <NUM> of the ground <NUM> below the winch <NUM> of the helicopter <NUM>.

When the winch <NUM> of the helicopter <NUM> is operated for lifting persons <NUM> and/or objects <NUM> from the ground <NUM>, it is desirable to illuminate the operational area <NUM> of the winch <NUM>, i.e. the area <NUM> of the ground <NUM> surrounding the persons <NUM> and/or objects <NUM> to be lifted, in order to reliably identify the persons <NUM> and/ or objects to be lifted and to allow for a safe operation of the winch <NUM>.

For coordinating the illumination of the operational area <NUM> of the winch <NUM> with the operation of the winch <NUM>, the lighting control device <NUM> may be coupled with the winch control system <NUM> for receiving commands for controlling the operation of the rotorcraft lighting equipment 2a-2d, 2a', 2a", <NUM> from the winch control system <NUM>.

Alternatively or additionally, the lighting control device <NUM> may comprise a winch operator input device <NUM>, which is configured for allowing crew members <NUM> operating the winch <NUM> to input control commands into the lighting control device <NUM> for coordinating the illumination in the operational area <NUM> with the operation of the winch <NUM>.

The crew members operating the winch <NUM>, the cockpit crew <NUM> and the automated anti-collision device <NUM> may control the distribution of light emitted by the lighting equipment 2a-2d, 2a', 2a", <NUM> independently of each other. , in the example depicted in <FIG>, the illumination of the power line <NUM> may be controlled independently of the illumination of the operational area <NUM> of the winch <NUM>.

As a result, any obstacles <NUM>, such as power lines <NUM>, located in the illuminable area <NUM> as well as the operational area <NUM> of the winch <NUM> may be illuminated in an optimized manner, respectively. In other words, adjusting the illumination of one portion of the illuminable area <NUM>, such as the operational area <NUM> of the winch <NUM>, does not deteriorate the illumination of other areas <NUM>, such as areas <NUM> around obstacles <NUM> in the pilot's field of view <NUM>.

In consequence, the illumination of the space surrounding the helicopter <NUM> may be individually adjusted to the current situation, resulting in an optimized illumination of all currently interesting parts of said space.

Claim 1:
Rotorcraft lighting equipment (2a-2d, 2a', 2a", <NUM>), comprising:
a plurality of lighting devices (2a-2d, 2a', 2a") configured to be mounted to an exterior of a rotorcraft (<NUM>), wherein each of the lighting devices (2a-2d, 2a', 2a") comprises a plurality of individually controllable lighting modules (<NUM>) which are configured for emitting light into different spatial directions, allowing to generate different light distributions of the light emitted by the pluralities of lighting modules (<NUM>) of the of the plurality of lighting devices (2a-2d, 2a', 2a"); and
a lighting control device (<NUM>) configured for individually controlling the operation of the pluralities of lighting modules (<NUM>) of the plurality of lighting devices (2a-2d, 2a', 2a"), depending on the respective spatial directions, for generating a desired light distribution, which is one of the different light distributions, of the light emitted by the pluralites of lighting modules (<NUM>).