EP2488414A2 - Feu d'avertissement pour aéronefs - Google Patents

Feu d'avertissement pour aéronefs

Info

Publication number
EP2488414A2
EP2488414A2 EP10768185A EP10768185A EP2488414A2 EP 2488414 A2 EP2488414 A2 EP 2488414A2 EP 10768185 A EP10768185 A EP 10768185A EP 10768185 A EP10768185 A EP 10768185A EP 2488414 A2 EP2488414 A2 EP 2488414A2
Authority
EP
European Patent Office
Prior art keywords
light
wide
angle
light source
aircraft
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP10768185A
Other languages
German (de)
English (en)
Inventor
Jean Blondeau
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
FTI Technologies GmbH
Original Assignee
FTI Technologies GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by FTI Technologies GmbH filed Critical FTI Technologies GmbH
Publication of EP2488414A2 publication Critical patent/EP2488414A2/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • B64D47/02—Arrangements or adaptations of signal or lighting devices
    • B64D47/06—Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B45/00—Circuit arrangements for operating light-emitting diodes [LED]
    • H05B45/10—Controlling the intensity of the light
    • H05B45/12—Controlling the intensity of the light using optical feedback
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B45/00—Circuit arrangements for operating light-emitting diodes [LED]
    • H05B45/30—Driver circuits
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D2203/00—Aircraft or airfield lights using LEDs
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F21—LIGHTING
    • F21W—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES F21K, F21L, F21S and F21V, RELATING TO USES OR APPLICATIONS OF LIGHTING DEVICES OR SYSTEMS
    • F21W2107/00—Use or application of lighting devices on or in particular types of vehicles
    • F21W2107/30—Use or application of lighting devices on or in particular types of vehicles for aircraft

Definitions

  • the invention relates to a warning light for aircraft, in particular for aircraft.
  • warning lights are to be mounted on the outside of an aircraft. Although each aircraft is appropriately illuminated so that its position and orientation can be seen by an observer in each position, there is a risk that the position and orientation of the aircraft may become unrecognizable as soon as any of these warning lights are malfunctioning or even malfunctioning completely fail.
  • xenon flash tubes are used, which sit under a protective hood, a so-called dome, with the dome mounted above the flash tube, which in turn projects beyond the aircraft's outer skin.
  • a dome serves to protect the xenon flash tubes on an aircraft from harmful influences in order to ensure their proper functioning as well as possible.
  • the dome increases the aerodynamic drag of the aircraft. Increased aerodynamic drag of the aircraft also results in higher fuel consumption. In order to reduce the consumption of fuel by the aircraft, therefore, there is a need for a warning light, which brings a lower air resistance with it.
  • the present invention provides a warning light for aircraft according to claim 1, an aircraft comprising a warning light according to the invention according to claim 15 and a use of the warning light on an aircraft according to claim 18 ready.
  • the warning light for aircraft comprises a light source and a wide-angle optic, wherein the light source is optically connected to the wide-angle optics.
  • the light source and the associated wide-angle optics form two separate elements.
  • a wide-angle optics for the warning light which is separate from the light source, does not require the entire warning light can be arranged on the outer skin of the aircraft, but the light source can also be arranged inside the aircraft, if there is an optical connection to the wide-angle optics.
  • the wide-angle optics fan out the light to be emitted, the wide-angle optics can be further sunk into the interior of the aircraft than would be possible with a xenon flash tube.
  • the wide-angle optic of the warning light according to the invention protrudes less strongly beyond the outer side of the outer skin of the aircraft than a xenon flash tube.
  • an aircraft with a warning light according to the invention has a lower air resistance than an aircraft with a xenon flash tube.
  • An aircraft may in particular be an airplane, a helicopter, a glider, a balloon or an airship.
  • the aircraft may be powered by an internal combustion engine and / or by an electric motor.
  • the aircraft may be suitable for carrying passengers and / or freight.
  • a warning light may be any lamp which is designed to identify the position and / or extent of the aircraft and / or its elements, in particular the position and / or extent of the fuselage, wings and / or tail.
  • the warning light can be permanently connected to the aircraft.
  • a warning light may in particular be a collision-proof light (sometimes also called anti-collision light or "anti-collision light”) or an identification light for marking the wings, the fuselage or the tailplane or tailplane it only temporarily emits light, for example in the form of a so-called "strobe light", or it can shine permanently.
  • the warning light for the emission of light signals for determining the position and / or the orientation of the aircraft, for example during the takeoff and / or landing phase may be formed. Furthermore, the warning light may be used to identify points from the outline of a ground-based or rolling aircraft, such as the nose and / or the tail, the tips of the wings, and / or the tailplane.
  • the light source is optically connected to the wide-angle optics, so that the light generated by the light source can be emitted via the wide-angle optics.
  • the light source may be arranged spatially separated from the place where light is emitted through the wide-angle optics to the outside.
  • the light source does not have to be spatially separated from the wide-angle optics.
  • the light source may be located in a place which is protected against external influences.
  • the light source may be electrically isolated from the wide-angle optic. Then the light source can be shielded against electrical influences on the wide-angle optics.
  • the wide-angle optics may be an optical device bounded by an entrance and an exit surface.
  • the wide-angle optics may be capable of deflecting a bundle of parallel light rays incident through the entrance surface by refraction and / or diffraction such that the light rays that leave the device through the exit surface after passing through the device diverge.
  • the wide-angle optics can have a focal plane.
  • the focal plane may include the amount of all pixels at which parallel rays of light entering the wide-angle optic through the exit surface intersect by the influence of wide-angle optics.
  • the area comprising the set of all the pixels where the wide-angle optics are capable of intersecting incident rays can be called an image area.
  • the terms of the pixel and the image area will be used hereafter.
  • the wide-angle optics may be an optical unit which serves to radiate incident light into a solid angle.
  • the wide-angle optics may include one or more lenses and / or one or more diffraction gratings. The deflection of light in the wide-angle optics can be done by diffraction or refraction.
  • the individual lenses in the wide-angle optics can consist of different types of glass, in particular crown glass or high-refractive silicate glasses. The glasses can be hardened.
  • the wide-angle lens system may contain lenses made of a plastic material, in particular of polycarbonate. The refractive indices of the lens materials can be at least 1.5, in particular also values of 1.8 or greater.
  • the direction of incidence of the light in the wide-angle optics can be defined as the direction in which a light beam impinges on the first optical element, for example a lens or a grating, in the wide-angle optics.
  • the space in which light is emitted through the wide-angle optics can cover a range of up to at least 60 degrees. cover over the direction of incidence of the light in the wide-angle optics.
  • the space area into which light is radiated may also cover a range of up to at least 75 degrees, 90 degrees or 110 degrees with respect to the direction of incidence of the light in the wide-angle optics.
  • the space in which light is emitted by the wide-angle optics may have the shape of a straight circular cone.
  • This cone can have as an axis an optical axis of the wide-angle optics.
  • the axis of the cone may be the optical axis of a wide-angle lens.
  • the opening angle of the circular cone may be twice the angle between a generatrix of the straight circular cone and its axis, the generatrix being a connecting line of a peripheral point on its base circle with the apex of the cone.
  • the wide-angle optics can be waterproof and / or airtight. In other words, it may be that no liquid can penetrate into the interior of the wide-angle optics, and / or that no gas exchange between the interior of the wide-angle optics and their environment can take place.
  • the wide-angle optics can be designed such that incident light is deflected by the wide-angle optics from the direction of incidence into the wide-angle optics by up to at least 60 degrees, in particular by up to at least 75 degrees or 90 degrees.
  • the wide-angle optics may include a wide-angle lens.
  • the wide-angle optics can be constructed rotationally symmetrical with respect to an optical axis, in other words, a rotation of the wide-angle optics by any angle about its optical axis is the wide-angle optics on itself.
  • the wide-angle optic may emit light into a spatial region that corresponds to a straight circular cone about its optical axis.
  • the opening angle of the straight circular cone can be at least 120 degrees, in particular at least 150 degrees.
  • the wide-angle optics can be a fisheye look. Then, the opening angle of the straight circular cone around its optical axis at least 180 degrees, in particular at least 220 degrees.
  • the light source may comprise at least one laser diode or a light emitting diode, LED.
  • the light source contains only one laser diode, it can emit coherent light. Alternatively or additionally, it may contain further laser diodes and / or light-emitting diodes.
  • the least A laser diode may be, for example, a pulse laser diode or a Q-switch laser diode.
  • a light emitting diode can emit incoherent light.
  • the light source may comprise at least two diodes, wherein the light source may comprise only laser diodes, only light emitting diodes, or a combination of laser diodes, light emitting diodes and / or other light generating semiconductor elements.
  • the use of semiconductor elements can result in a weight saving over xenon lights according to the prior art.
  • the use of semiconductor elements can also result in a reduction of the maintenance effort compared to xenon lights according to the prior art.
  • the light source may comprise at least two laser diodes or at least two light emitting diodes or comprise a combination of at least one laser diode with at least one light emitting diode. These multiple diodes can emit light of different colors. In particular, the light source may comprise three different-colored diodes in the colors red, green and blue.
  • the light source can emit red light or white light.
  • the light source may comprise a single diode emitting red or white light.
  • the diode may be a laser diode or a light emitting diode.
  • red light may have a wavelength which is less than or equal to 700 nm, in particular less than or equal to 670 nm, and greater than or equal to 650 nm.
  • a red diode as a luminous element, it may be possible to dispense with a color filter for generating red light.
  • the hue of the emitted red light may correspond in particular to the specifications for the hue "Aviation red” according to general aviation regulations, in particular FAR Part 25 sec. 25.1397.
  • the light source can emit white light, which can be a composite of radiation from different wavelength ranges.
  • the light source may include three diodes emitting red, green and blue radiation. Each of the three diodes may be a laser diode or a light emitting diode. Contributions to the white light may originate from radiation components with intensity maxima at different wavelengths, in particular in the ranges between 430 nm and 460 nm, 540 nm and 570 nm and / or 590 to 620 nm.
  • the white light may be emitted by a single diode, which emits light of a color and converts a phosphor.
  • the hue of the emitted white light may correspond in particular to the specifications for the hue "Aviation white” according to general aviation regulations, in particular FAR Part 25 sec. 25.1397.
  • the light source can be connected to the wide-angle optic via a light guide.
  • the cross-section of the region of the light guide which is available for the transmission of light may cover at least the area of the image area of the wide-angle optics.
  • the end face of the light guide may be in the focal plane of the wide-angle optic.
  • the cross section of the exiting light beam may comprise the image area of the wide-angle optics. This may make it possible to radiate the light emitted by the wide-angle optics into a large spatial area.
  • the light guide may be made of plastic material, for example, in particular polystyrene or polymethyl methacrylate, or glass fiber, in particular mineral glass. Different regions of the light guide can have different refractive indices.
  • the light guide may be a gradient index fiber and / or a devisnindexfa- ser.
  • the light guide may consist of a bundle of light-conducting fibers. This can be achieved in particular a larger light pipe cross-section and thus an improved adaptation to the wide-angle optical system.
  • the fibers may have different refractive indices.
  • the fibers may be gradient index fibers and / or step index fibers. With a fiber bundle, it may be possible to transport higher light intensities than with a fiber that consists of a single fiber.
  • the light guide may have an electrically insulating sheath.
  • the sheath may comprise, for example, Teflon.
  • the sheath can serve for mechanical stiffening and / or increase the mechanical resistance of the light guide.
  • the sheathing can prevent the optical fiber from being bent so much that it damages or damages its own Change light pipe properties. Due to the insulating property of the jacket, propagation of leakage currents to the optical fiber can also be prevented, in particular in the event of a lightning strike in the warning light or close to the warning light. As a result, damage can be prevented in particular by heating the optical fiber by leakage currents.
  • the warning light may further comprise a control unit, wherein the control unit is configured to cause the light source to emit light.
  • the control unit may be configured to control the light source.
  • the control unit may be configured to cause the light source to emit light of constant intensity.
  • the control unit may be configured to cause the light source to change the intensity of the emitted light.
  • the control unit may also be designed to cause the light source to change the spectral distribution of the intensity of the emitted light.
  • the control unit may be configured to cause the light source to repeatedly emit light signals for limited time intervals.
  • the control unit may in particular be designed to cause the light source to emit a flashing light or a strobe light. Then the warning light does not emit light constantly, but it can time intervals during which the warning light emits light, alternate with time intervals during which the warning light emits no light.
  • the time intervals during which the light source emits light may all be of equal length or varying in length.
  • the time intervals during which the light source emits light can be as long as the intervals at which it emits no light.
  • the time intervals during which the light source emits light may have a different length than those to which the light source does not emit light.
  • the length of the time intervals at which the light source emits light may change over time or be constant over time.
  • a time interval during which the light source emits light may be shorter than 1 second, in particular less than 0.1 seconds or less than 0.001 seconds.
  • a time interval during which the light source does not emit light may be shorter than 2 seconds, in particular shorter than 0.5 second or shorter than 0.1 second.
  • a sequence of time intervals at which the warning light emits light and to which it emits no light may be repeated periodically.
  • the time intervals during which the warning light emits light as a flashing light can be so small that the warning light can light up at least 30 times in one minute. In particular, the time intervals can be so small that the warning light can light up to 110 times per minute.
  • the warning light may be used as an anti-collision light in accordance with aviation regulations (for example, See, 25.1401). It may also be possible to use the warning light as a flashlight to identify the wings (Wing Strobe Lights) or the tail (Tail Strobe Light) according to aviation regulations.
  • the intensity of the radiated light may comply with aviation regulations, in particular sea. 25.1401. This may mean, in particular, that effective intensities of the emitted light reach at least the values prescribed in accordance with aviation regulations.
  • the effective intensity l e of the warning light as a flashing light can be determined in particular according to the following formula:
  • the effective intensities of the warning light when used as a flashing light can reach at least the following values, depending on the angle of radiation with respect to the horizontal plane of the aircraft:
  • the warning light may comprise a feedback device, which is designed such that a portion of the light, which is intended to be emitted by the wide-angle optics, is measured, whereby a feedback to the light source takes place based on the measurement result.
  • the feedback unit can measure light provided for transmission by the wide-angle optics and, based thereon, cause a change in the light source.
  • the feedback unit may cause the change in the light source by forwarding a signal to the control unit.
  • the signal can be an electrical signal.
  • the feedback unit can comprise at least one feedback optical fiber or a light-conducting element, wherein the feedback optical fiber and / or the light-conducting element for the extraction of light can be brought into the range from which light is to be taken for the measurement.
  • the part of the light to be measured can be taken from the light beam in the entrance area of the wide-angle optics.
  • the area where the light is taken for the measurement can be within the wide-angle optics, in particular between optical elements such as lenses or gratings within the wide-angle optics.
  • the light for the measurement can also be taken from the light behind the wide-angle optics, in particular from light, which has passed in the beam path of the wide-angle optics, the last optical element of the wide-angle optics.
  • the light can also be taken from the surface of this last optical element.
  • the extracted light for the measurement can be returned to at least one feedback sensor via at least one feedback optical fiber.
  • the at least one feedback sensor may be integrated in the control unit.
  • the at least one feedback sensor may convert the light returned via the at least one feedback optical fiber into at least one electrical signal.
  • the control unit may control the light source.
  • the control unit can cause the light source in particular to increase or decrease the intensity of the light generated.
  • the control unit can in particular also cause the light source to change the spectral distribution of the intensity of the light generated.
  • the control unit can in particular also change the time intervals during which it causes the light source to emit light signals.
  • the feedback device may include at least one feedback sensor and at least one electrical feedback line.
  • the at least one feedback sensor can be arranged, in particular, at at least one of the points described above, at which light for the measurement can be taken.
  • the at least one feedback sensor can convert light into electrical signals.
  • the control unit may regulate the light source. In particular, it can cause the light source to change the intensity and / or the spectral distribution of the intensity of the light generated.
  • the warning light may further comprise a beam widening optical system, wherein the light source is connected to the wide-angle optical system via the beam widening optical system.
  • the beam expanding optics can increase the cross section of the light beam coming from the light source.
  • the beam expanding optics may increase the cross section of the beam incident in the wide angle optics to cover at least the area of the image area of the wide angle optics.
  • the light can be passed through at least one light guide.
  • the light source can be optically connected directly to the wide-angle optic via a beam expansion optics.
  • the light source can be connected to the wide-angle optics via the beam widening optics, without there being a connection between a light guide and a beam widening optics or between beam widening optics and wide-angle optics.
  • the light source can be mechanically connected directly to the beam expansion optics and these directly to the wide-angle optics, in particular glued or screwed.
  • the warning light may include a plurality of wide-angle optics that are optically connected to the light source.
  • the characteristics of the wide-angle optics in the above-described embodiments of the warning light may apply to each of the plurality of wide-angle optics.
  • the plurality of wide-angle optics may be capable of deflecting incident light by refraction or diffraction into a straight circular cone about its optical axis.
  • one of the embodiments described above for the connection between the light source and a wide-angle optical system can be used for the connection between the light source and the plurality of wide-angle optics.
  • the light source may be connected to at least one of the plurality of wide-angle optics via a light guide, and / or the light source may be connected to at least one of the plurality of wide-angle optics via a beam expansion optics.
  • the light In front of or behind the beam widening optics, or in front of and behind the beam widening optics, the light can be transmitted with light guides.
  • the beam entry into the wide-angle optics, and / or within the wide-angle optics, and / or behind the beam exit from the wide-angle optics in at least one of the plurality of wide-angle optics from the beam for the radiation through this wide-angle optics.
  • Optics is provided, light is removed and fed into a feedback optical fiber.
  • the at least one feedback optical fiber may pass light to at least one feedback sensor.
  • the at least one feedback sensor may convert the input light into at least one electrical signal.
  • a control unit can regulate the light source.
  • the light source may comprise only 1 diode, or 3 diodes for generating white light.
  • the invention also provides an aircraft comprising a warning light as described above.
  • the aircraft may also include a plurality of warning lights according to the invention.
  • the warning lights may be arranged so that the light emitted by them is radiated in each direction to a range of at least 60 degrees above and at least 60 degrees below the horizontal plane of the aircraft, in particular within 75 degrees above and 75 degrees below the horizontal plane.
  • it may be that the emitted light does not reach a spatial region comprising a solid angle of 0.04 steradian, in particular 0.03 steradian maximum, which lies within a solid angle of maximum 0.20 steradian, in particular maximum 0.15 steradian, which is directed in the backward direction of the aircraft and centered around the longitudinal axis of the aircraft.
  • the light source may be located inside the aircraft.
  • the light source may be located inside the aircraft at a shielded location.
  • the light source can be protected in particular against environmental influences such as moisture, temperature fluctuations or electromagnetic fields.
  • the light source can thus be shielded against the consequences of a lightning strike.
  • the wide-angle optics may be arranged flush with the outer skin of the aircraft and / or the wide-angle optics may be arranged so that it does not project beyond the outer side of the outer skin of the aircraft.
  • the wide-angle optics can be arranged so that only a part of their length protrudes from the fuselage, in particular only 70%, or only 20%.
  • the wide-angle optics can be sunk completely in the fuselage of the aircraft.
  • the wide-angle optics may be recessed in the fuselage of the aircraft or in a wing or tail, in particular, its outermost optical element may be flush with the aircraft fuselage, wing or tail.
  • the wide-angle optics can also be installed in an opening in the aircraft fuselage, wing or tail.
  • the wide-angle optics may include a protection device.
  • a protective device may be a protective hood, which covers an opening in the outer skin of the aircraft, which is provided for the warning light or the wide-angle optics, in particular a dome.
  • the protective cover can be made of glass, plastic or another transparent material.
  • the protective hood can be fastened to the aircraft fuselage and / or to the wide-angle optics and / or to the light source and / or to a control unit for the light source.
  • a protective device can also be a protective glass, which is integrated as the ultimate element in the wide-angle optics.
  • the outermost element of the wide-angle optic may be that element in the wide-angle optic through which the light to be emitted passes last before leaving the wide-angle optic.
  • a protective device can also be a lightning rod.
  • a protective device may also be a closure which closes the opening in which the wide-angle lens system is installed, for example a protective screen.
  • a protective device can also be a seal which seals at least parts of the warning light, in particular the wide-angle lens, or the opening into which at least parts of the warning light, in particular the wide-angle lens, are incorporated. Such a seal may be made of rubber or a plastic.
  • the protection device can cause no gas exchange between the interior of the wide-angle optics and its environment can take place. The protection device may also cause moisture to not penetrate into the wide-angle lens.
  • the invention provides the use of one of the previously described warning lights on an aircraft.
  • Figure 1 shows schematically an example of a warning light according to the invention with a
  • Figure 2 shows schematically an example of a warning light according to the invention with several wide-angle optics.
  • FIG. 3 schematically shows an example of a warning light according to the invention with the use of a beam widening optical system.
  • Figure 1 shows an example of an embodiment of the invention installed in the fuselage 160 of an aircraft, such as an aircraft.
  • a light source 110 having a red, a green and a blue laser diode is connected to a wide-angle optical system 120 via a light guide 130. Under certain circumstances, several of these three laser diodes may be provided.
  • the light source is regulated by a control unit 140.
  • the wide-angle optic has a fish-eye characteristic, i. it is constructed rotationally symmetrical with respect to its optical axis and is able to divert incident light into a straight circular cone whose axis forms the optical axis 190 of the wide-angle optical system, with an aperture angle of at least 170 degrees.
  • the opening angle of the circular cone denotes twice the angle between a surface line of the straight circular cone and its axis, wherein the surface line is a connecting line of a boundary point on the base circle of the cone with the apex.
  • the wide-angle lens is designed so that the outer side 175 of its outlet element 170 is designed flush with the outer side 165 of the aircraft fuselage 160.
  • the exit element is the optical element of the wide-angle optical system 120, which is traversed last by the light, before the light to be emitted, after passing through the wide-angle optical 120 again outside the wide-angle optical 120.
  • a feedback light guide 150 Integrated into the exit element 170 is a feedback light guide 150. It could also be integrated elsewhere in the wide-angle optic. It connects the exit element 170 with the feedback sensor 141, which is integrated in the control unit 140. By returning light via the feedback optical fiber 150 to the feedback sensor 141, the control unit 140 can independently control the light source so that parameters of the emitted light remain within predetermined limits.
  • the light source 110 is designed to emit white light. This is achieved by suitable control of the three diodes.
  • the light source for generating white light could also include a laser diode or light emitting diode, which is provided with a white Light emitting phosphor is equipped.
  • the light source is controlled by the control unit 140.
  • the control unit can change the hue of the emitted light by separately controlling the radiation intensity for each of the three diodes involved.
  • the control unit can regulate the total intensity of the emitted light, for example by similar changes in the radiation intensity in all three diodes.
  • the light source is designed to emit red light.
  • the control unit causes the light source to emit light in the manner of a stroboscope.
  • a single flash of light can have a duration of 1 ps. Longer flash periods or a continuous emission of light is also possible.
  • the light source 1 10 emits light, which is radiated into the light guide 130.
  • the end surface 180 of the light guide lies in the focal plane of the wide-angle optics.
  • the cross section of the region of the optical waveguide in which it is available for light conduction comprises the cross section of the image region of the wide-angle optical system.
  • the light guided through the light guide exits the light guide 130 at the end face 180 of the light guide, which lies in the focal plane of the wide-angle lens, and enters into the wide-angle lens 120.
  • the light entering the wide-angle optics from the light guide is deflected there and passes over the exit surface 175 of the exit element 170 at an angle between 0 degrees and at least 85 degrees (half the opening angle of the above-mentioned circle cone) with respect to the optical axis 190 the wide-angle optics 120 off.
  • the exit surface 175 is formed by the part of the surface of the exit element 170 that is not covered and points outward, ie not into the interior of the wide-angle lens.
  • the feedback optical fiber 150 redirects light from the exit member 170 back to a feedback sensor 141. This contains feedback on the intensity and the color of the light, which is emitted to the outside. Depending on the received light, the feedback sensor generates an electrical signal. Based on this electrical signal, the control unit 140 may compensate for variations in intensity, such as clouding at the exit element 170, and / or color variations. The existence of the feedback optical fiber and the feedback sensor can also be dispensed with.
  • FIG. 2 shows a further embodiment of the invention.
  • a light source 210 is included, which includes a laser diode with red radiation. The laser diode could also emit radiation of other color.
  • the light source is controlled by the control unit 240.
  • two wide-angle optics 220, 221 are installed at different locations such that the exit surfaces 275, 276 of the exit elements 270, 271 of the wide-angle telescopes 220, 221 are flush with the outer side 265 of the aircraft 260.
  • the exit elements 270, 271 are the optical elements of the wide-angle optics 220, 221, which are last traversed by the light before the light to be emitted is again outside the respective wide-angle optics after passing through the wide-angle optics 220 and 221.
  • the exit surfaces 275, 276 are formed by the parts of the surface of the respective exit elements 270, 271 that are not covered and that face outwards, that is, not into the interior of one of the wide-angle optics 270, 271.
  • a light guide 230 leads to the wide-angle optic 220 and a second light guide 231 leads from the light source 210 to the wide-angle optic 221.
  • the connection of the wide-angle optic 220 with the light guide 230 and the connection of the wide-angle optic 221 with the Optical fiber 231 takes place in the same manner as described in connection with FIG.
  • the light guides 230, 231 terminate with their end faces 280, 281 in the focal planes of the wide-angle optics 220, 221.
  • the respective cross-section of the region of the light guide 230, 231 available for light guidance comprises the cross-section of the image area of the respective ones Wide-angle optics 220, 221.
  • the light from the light source 210 is emitted through both the wide-angle optic 220 and the wide-angle optic 221.
  • From the exit element 270 of the wide-angle optic 220 light is directed via the feedback optical fiber 250 to the feedback sensor 241 in the control unit 240.
  • the exit element 271 of the wide-angle optical system 221 guides light via the feedback optical fiber 251 to the feedback sensor 246 in the control unit 240.
  • the control unit 240 can independently control the light source 210 so that parameters of the emitted light remain within predetermined limits.
  • the control unit 240 may regulate the intensity of the light source 210.
  • the use of feedback optical fiber 250 with feedback sensor 241 and / or the use of feedback optical fiber 251 with feedback sensor 246 may also be eliminated.
  • FIG. 3 shows a further embodiment of the invention.
  • the light source 310 includes a laser diode.
  • the light source may also include an LED in another embodiment.
  • the light source 310 is connected to a beam expanding optics 305.
  • the beam expansion optics 305 fulfill the task of increasing the cross section of the light beam emerging from the light source 310.
  • the beam expanding optics 305 is further connected to a wide-angle optic 320.
  • the wide-angle optic 320 is installed in the fuselage 360 of an aircraft.
  • the exit element 370 of the wide-angle optical system 320 protrudes slightly from the outside 365 of the aircraft wall.
  • the exit element 370 is the optical element of the wide-angle optical system 320, which is traversed last by the light before the light to be emitted is again outside the wide-angle optical system 320 after passing through the wide-angle optical system 320.
  • the area in which the wide-angle optic protrudes from the outer wall of the aircraft is covered by a transparent protective hood 395.
  • the protective hood can have an aerodynamically advantageous shape.
  • the exit surface 375 is formed by the part of the surface of the exit element 370 that is not covered and points outward, ie not into the interior of the wide-angle lens.
  • the beam expansion optics 305 increases the cross section of the light beam to its end face 380 at least so much that it covers the image area of the wide-angle optics in the focal plane of the wide-angle optics 320 located there.
  • the light entering from the beam expansion optics 305 is fanned out.
  • the fanned-out light leaves the wide-angle optic through the exit surface 375 of the exit element 370.
  • the deflection of the light in the wide-angle optics is so strong that the light, after passing through the exit surface 375, is at an angle between 0 degrees and at least 85 degrees with respect to the optical Axis 390 of the wide-angle lens 320 is emitted.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Non-Portable Lighting Devices Or Systems Thereof (AREA)

Abstract

La présente invention concerne un feu d'avertissement pour aéronefs, qui comprend une source de lumière et une optique grand-angle, la source de lumière étant reliée optiquement à l'optique grand-angle.
EP10768185A 2009-10-12 2010-10-07 Feu d'avertissement pour aéronefs Withdrawn EP2488414A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009049112A DE102009049112A1 (de) 2009-10-12 2009-10-12 Warnlicht für Luftfahrzeuge
PCT/EP2010/006142 WO2011045001A2 (fr) 2009-10-12 2010-10-07 Feu d'avertissement pour aéronefs

Publications (1)

Publication Number Publication Date
EP2488414A2 true EP2488414A2 (fr) 2012-08-22

Family

ID=43798760

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10768185A Withdrawn EP2488414A2 (fr) 2009-10-12 2010-10-07 Feu d'avertissement pour aéronefs

Country Status (3)

Country Link
EP (1) EP2488414A2 (fr)
DE (1) DE102009049112A1 (fr)
WO (1) WO2011045001A2 (fr)

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DE102013103369B4 (de) * 2013-04-04 2017-05-04 Airbus Operations Gmbh Außenstrukturbauteil für ein Flugzeug, Flugzeug mit einem Außenstrukturbauteil und Verfahren zum Herstellen eines Außenstrukturbauteils für ein Flugzeug
EP3002221B1 (fr) * 2014-10-02 2019-03-13 Goodrich Lighting Systems GmbH Unité d'éclairage du sol pour aéronef et aéronef comprenant celle-ci
FR3034079B1 (fr) 2015-03-27 2018-09-07 Airbus Helicopters Systeme d'eclairage d'un aeronef et aeronef
FR3034080B1 (fr) * 2015-03-27 2017-11-10 Airbus Helicopters Systeme d'eclairage d'un aeronef et aeronef

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DE9117049U1 (de) * 1991-02-22 1995-05-11 Hella Kg Hueck & Co, 59557 Lippstadt Flache, beleuchtete Warn- oder Anzeigeeinrichtung
FR2680751A1 (fr) * 1991-09-03 1993-03-05 Thomson Csf Procede d'evitement des collisions pour des porteurs cooperatifs et ensemble optique embarque destine a sa mise en óoeuvre.
FR2714886B1 (fr) * 1994-01-10 1996-03-29 Labinal Dispositif de signalisation lumineuse sur aéronef.
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Also Published As

Publication number Publication date
WO2011045001A3 (fr) 2011-09-15
WO2011045001A2 (fr) 2011-04-21
DE102009049112A1 (de) 2011-04-21

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