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
  • B64D47/04—Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
• • 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
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F21—LIGHTING
  • F21V—FUNCTIONAL FEATURES OR DETAILS OF LIGHTING DEVICES OR SYSTEMS THEREOF; STRUCTURAL COMBINATIONS OF LIGHTING DEVICES WITH OTHER ARTICLES, NOT OTHERWISE PROVIDED FOR
  • F21V19/00—Fastening of light sources or lamp holders
  • F21V19/04—Fastening of light sources or lamp holders with provision for changing light source, e.g. turret
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F21—LIGHTING
  • F21V—FUNCTIONAL FEATURES OR DETAILS OF LIGHTING DEVICES OR SYSTEMS THEREOF; STRUCTURAL COMBINATIONS OF LIGHTING DEVICES WITH OTHER ARTICLES, NOT OTHERWISE PROVIDED FOR
  • F21V29/00—Protecting lighting devices from thermal damage; Cooling or heating arrangements specially adapted for lighting devices or systems
  • F21V29/50—Cooling arrangements
  • F21V29/70—Cooling arrangements characterised by passive heat-dissipating elements, e.g. heat-sinks
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F21—LIGHTING
  • F21V—FUNCTIONAL FEATURES OR DETAILS OF LIGHTING DEVICES OR SYSTEMS THEREOF; STRUCTURAL COMBINATIONS OF LIGHTING DEVICES WITH OTHER ARTICLES, NOT OTHERWISE PROVIDED FOR
  • F21V29/00—Protecting lighting devices from thermal damage; Cooling or heating arrangements specially adapted for lighting devices or systems
  • F21V29/50—Cooling arrangements
  • F21V29/70—Cooling arrangements characterised by passive heat-dissipating elements, e.g. heat-sinks
  • F21V29/74—Cooling arrangements characterised by passive heat-dissipating elements, e.g. heat-sinks with fins or blades
• • 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
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F21—LIGHTING
  • F21Y—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES F21K, F21L, F21S and F21V, RELATING TO THE FORM OR THE KIND OF THE LIGHT SOURCES OR OF THE COLOUR OF THE LIGHT EMITTED
  • F21Y2113/00—Combination of light sources
  • F21Y2113/30—Combination of light sources of visible and non-visible spectrum
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F21—LIGHTING
  • F21Y—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES F21K, F21L, F21S and F21V, RELATING TO THE FORM OR THE KIND OF THE LIGHT SOURCES OR OF THE COLOUR OF THE LIGHT EMITTED
  • F21Y2115/00—Light-generating elements of semiconductor light sources
  • F21Y2115/10—Light-emitting diodes [LED]

Definitions

• This invention relates to dual-mode visible and infrared lighting. Specifically, this invention relates to a dual mode visible and infrared lighthead for use with aircraft landing lights and searchlights, and for use with other vehicles.
• Aircraft generally have landing lights mounted thereon to provide illumination during taxi, take-off, and landing when visibility is reduced by darkness or adverse weather conditions.
• Landing lights may be mounted in a fixed position on the aircraft; alternatively, the landing lights may be pivotable by drive means to extend from the aircraft when needed, and retracted to reduce drag when not in use.
• Searchlights are pivotable by drive means similar to landing lights, but include an additional capability to rotate up to 360 degrees in a plane perpendicular to the extend-retract plane.
• Military and law enforcement helicopters commonly use searchlights to aim a beam of light in a desired direction to illuminate targets.
• prior dual mode lightheads utilize visible light sources coupled with infrared filters to produce the infrared light, generating high temperatures within the lighthead that can limit the life of the light elements, lenses, and sealing materials.
• a dual mode lighthead that is easier to maintain, provides higher intensity light output, and operates at a lower temperature to extend lighthead component life.
• This invention is directed to a dual mode lighthead that is easier to re-lamp, provides improved light output, and generates less heat as compared to prior dual mode lightheads.
• the present invention is a modular design incorporating a housing, preferably a cast aluminum housing.
• the housing is designed to accommodate installation of the lighting elements from the rear of the lighthead. This prevents contamination of the reflector with dirt, oil, or fingerprints that can reduce the optical efficiency of the reflector. Installing the lighting elements from the rear also reduces maintenance time, since the front lens does not have to be removed and then re-sealed.
• the present invention utilizes a visible light source that includes a base that allows maintenance personnel to handle and install the lamp from the rear of the lighthead without touching or otherwise contaminating the glass envelope. Further, the lamp base allows the visible light source to be easily installed and removed without the need for tools.
• the invention also utilizes high intensity infrared diodes in contrast to the filtered visible light sources used in prior lightheads.
• High intensity infrared diodes offer increased infrared light emission along with higher efficiency, reduced power consumption, longer life, and reduced heat generation.
• the high intensity infrared diodes also facilitate faster and simpler replacement due to their modular design.
• the present invention comprises a dual mode lighthead, comprising: a housing comprising front, rear, top, and bottom sectors; an attachment point connected with one of said sectors of said housing to connect the dual mode lighthead with means for positioning the lighthead; means for reflecting light mounted inside said housing, said means positioned to reflect light from the front sector of said housing; at least one high intensity infrared diode, said diode being installed into said housing from the rear sector of said housing and positioned to emit infrared light out of the front sector of said housing; at least one visible light source, said visible light source being installed into said housing from the rear sector of said housing such that said visible light source projects through said reflectors and emits light from the front sector of said housing; and at least one lens affixed to the front sector of said housing through which one of emitted visible and infrared light passes.
• Figures 1 -a and 1 -b are views of the back and cover of the dual mode lighthead
• Figure 2 is a view of the visible light source
• Figure 3 is a view of the front of the dual mode lighthead
• Figure 4 is an electrical schematic of the dual mode lighthead.
• Dual mode lighthead 100 includes a housing 102 having a rear sector 128, a top sector 124, and a bottom sector 126. Housing 102 also includes a front sector 122, shown in Figure 3 and discussed below. Housing 102 is comprised of a cast or machined material, preferably aluminum, and may optionally include a plurality of cooling fins 104 to aid in the dispersion of heat generated by the light sources. Housing 102 further includes the parabolic reflector cavities 106 shaped to optimize the optical design for the visible light portion of lighthead 100 wherein the visible light is emitted from the front sector 122 of housing 102.
• Lamp retainer slots 130 are cast or machined into the reflector cavities 106 to facilitate installation of the visible light sources 200, discussed in greater detail below. Cavities 106 may also optionally include a plurality of heat-sink ribs 108 to help carry away heat generated by the visible light sources.
• the openings 1 10 accommodate the infrared light sources, and the openings 1 12 accommodate the visible light sources of lighthead 100.
• An attachment point 1 14 is affixed to the bottom sector 126 of housing 102 and facilitates mounting of lighthead 100 directly to the aircraft structure, or optionally to the pivot means of a landing light or searchlight.
• a rear cover 1 16 protects the interior of lighthead 100 from the elements, being secured with a plurality of screws 1 18 to the receptacles 120.
• the visible light source 200 is shown in Figure 2.
• An incandescent lamp 202 preferably halogen, is affixed to a lamp base 204.
• the lamp base 204 provides a convenient surface for handling the visible light source 200 without contaminating the lamp 202.
• One or more retaining springs 206 are attached to the lamp base 204 by conventional means such as rivets 208.
• the lamp leads 210 facilitate connection of electrical power to the lamp 202.
• the infrared light sources 302 preferably high intensity infrared diodes
• the visible light sources 200 preferably halogen lamps
• the retaining springs 206 spread and then snap into the lamp retainer slots 130, firmly holding the visible light source 200 in place.
• the cast aluminum reflectors 306 are installed into cavities 106 to optimize light emission from visible light sources 200.
• the lenses 308 are installed onto the front sector 122 of housing 102 and sealed to protect the interior of lighthead 100 from the elements.
• the attachment point 1 14 is affixed to the bottom sector 126 of housing 102 and facilitates mounting of lighthead 100 directly to the aircraft structure, or optionally to the pivot mechanism of a landing light or searchlight.
• electrical power for the dual mode lighthead is supplied by the power input lines 416, 418. Electrical power is controlled by a switch 402, which provides logical electrical input signals to the logic circuit 410 of the control circuit 400 via the logic lines 420, 422. If logic circuit 410 detects the presence of an electrical voltage on the "visible" logic line 420, the electronic switch 412, such as a power metal oxide semiconductor field effect transistor (MOSFET), is activated, causing the visible light sources 200 to emit visible light. If logic circuit 410 detects the presence of an electrical voltage on the "NVIS" logic line 422, the driver control 414 activates the driver 408.
• MOSFET power metal oxide semiconductor field effect transistor
• the driver 408, such as an electrical current limiter, supplies a controlled amount of electrical current to the infrared light sources 302, causing the infrared light sources 302 to emit infrared light.
• the logic circuit 410 turns off both the visible light sources 200 and the infrared light sources 302 when no voltage is detected on either of the logic lines 420, 422.
• the logic circuit 410 also turns off both the visible light sources 200 and the infrared light sources 302 if an illegal logic condition exists, such as voltage present on both logic lines 420, 422.
• the high-voltage protection filter 404 isolates electrical noise between the aircraft and the control circuit 400.
• the power supply 406, such as a voltage regulator, conditions the power from the aircraft to a voltage level suitable for the components in control circuit 400.
• the dual mode lighthead is mounted to a fixed or retractable landing light mechanism, or a searchlight mechanism.
• a control switch 402 located in the cockpit, is typically in the "Off" position causing electrical power to be rernoved from both the visible lamps 200 and the infrared light sources 302.
• electronic switch 412 is activated, applying power to the visible light sources 200 and causing them to emit a bright visible light.
• driver 408 is actuated, causing the infrared light sources 302 to emit infrared light to facilitate searching, targeting, and landing during covert operations.
• the present invention has been shown and described herein with reference to a particular embodiment for a particular application, the present invention is not limited to aviation uses. Indeed, the present invention is immediately applicable to hand-held and stationary fixtures as well as all types of vehicular traffic, including automotive, marine, and railroad.

Landscapes

• Engineering & Computer Science (AREA)
• General Engineering & Computer Science (AREA)
• Aviation & Aerospace Engineering (AREA)
• Arrangement Of Elements, Cooling, Sealing, Or The Like Of Lighting Devices (AREA)
• Glass Compositions (AREA)
• Lighting Device Outwards From Vehicle And Optical Signal (AREA)
• Non-Portable Lighting Devices Or Systems Thereof (AREA)
• Fastening Of Light Sources Or Lamp Holders (AREA)

Priority Applications (5)

Applications Claiming Priority (4)

Publications (1)

Family

ID=26945832

Family Applications (1)

Country Status (10)

Cited By (2)

Families Citing this family (34)

Citations (4)

Family Cites Families (18)

• 2001
  • 2001-08-17 US US09/932,342 patent/US6609812B2/en not_active Expired - Lifetime
  • 2001-12-04 CA CA002432647A patent/CA2432647A1/en not_active Abandoned
  • 2001-12-04 JP JP2002551430A patent/JP2004526614A/ja not_active Withdrawn
  • 2001-12-04 DK DK01995456T patent/DK1343690T3/da active
  • 2001-12-04 AT AT01995456T patent/ATE328791T1/de not_active IP Right Cessation
  • 2001-12-04 EP EP01995456A patent/EP1343690B1/en not_active Expired - Lifetime
  • 2001-12-04 WO PCT/US2001/047295 patent/WO2002049915A1/en not_active Ceased
  • 2001-12-04 DE DE60120472T patent/DE60120472T2/de not_active Expired - Lifetime
  • 2001-12-04 KR KR10-2003-7008450A patent/KR20030063458A/ko not_active Withdrawn
  • 2001-12-20 TW TW090131661A patent/TWI257990B/zh not_active IP Right Cessation

Patent Citations (4)

Also Published As

Similar Documents

Legal Events