CN110844040A - Aircraft body lighting system - Google Patents
Aircraft body lighting system Download PDFInfo
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- CN110844040A CN110844040A CN201911033857.2A CN201911033857A CN110844040A CN 110844040 A CN110844040 A CN 110844040A CN 201911033857 A CN201911033857 A CN 201911033857A CN 110844040 A CN110844040 A CN 110844040A
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- light
- luminous
- emitting
- aircraft
- control
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D5/00—Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures
- B05D5/06—Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures to obtain multicolour or other optical effects
- B05D5/061—Special surface effect
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D5/00—Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures
- B05D5/12—Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures to obtain a coating with specific electrical properties
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
Abstract
The invention provides an aircraft body light-emitting system. The aircraft mainly comprises an engine body light-emitting control unit, an engine body light-emitting power supply manager, a flight control computer, a light sensor and a light-emitting coating block. The luminous coating block comprises a luminous area and a circuit area, and is powered by the body luminous power manager to drive the electroluminescent coating to emit light; the machine body light-emitting control unit performs switching control on a light-emitting system working mode and a light-emitting control scheme; the flight control computer determines a light-emitting control scheme according to a preset program, and the power supply control is carried out through the light-emitting power manager of the aircraft body. The invention has the advantages of convenient implementation, little influence on the pneumatic appearance, adaptability to various irregular machine body appearances, designable luminous patterns, adjustable luminous characteristics and real-time switching of the luminous control scheme.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to an aircraft body light-emitting system.
Background
With the development of aerospace technology, aircrafts such as airplanes, airships, balloons, satellites and the like are widely applied to the civil and military fields. The aircraft body emits light with specific color, brightness and pattern, or changes the color, brightness and pattern, or flickers regularly, and can be used for self identification, visual invisibility, information transmission, advertising, flight performance, etc.
At present, various aircrafts mainly emit light through various lamps with limited installation quantity, the application range is limited to the identification of the aircrafts, and some small aircrafts also emit light on the airframe by using LED luminescent lamps, electroluminescent films, fluorescent paints and the like for performing. However, the LED light-emitting lamp is a point light source, is arranged outside the aircraft to influence the aerodynamic appearance of the aircraft body, is arranged inside the aircraft to occupy space, requires the aircraft body to be transparent, and is inconvenient to use and install on the aircraft body in a large range; the electroluminescent film can be paved on the flat shape of the surface of the aircraft body, but is difficult to be applied to the irregular shape of the aircraft body; the fluorescent paint can be used in a large range, but has low brightness, uncontrollable luminous characteristics and more application limitations. These factors all limit the application of aircraft airframes to glow.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides an aircraft body lighting system. The invention has convenient implementation, little influence on the pneumatic appearance, can adapt to various irregular organism appearances, and the luminous pattern can be designed, the luminous characteristic (brightness, flicker rule, etc.) can be adjusted, and the luminous control scheme can be switched in real time.
The utility model provides an aircraft organism lighting system, mainly includes organism luminous control unit, organism luminous power manager, flight control computer, light sensor, luminous coating piece, its characterized in that: the luminous coating block comprises a luminous region and a circuit region, the luminous region comprises an electroluminescent coating sprayed on a designated part of the aircraft body, the circuit region comprises a circuit connecting region, an anode and cathode isolating region, an anode and a cathode, and the body luminous power manager supplies power to drive the electroluminescent coating to emit light; the body light-emitting control unit is used for carrying out switching control on the on and off of a light-emitting system and a working mode and a light-emitting control scheme; the flight control computer determines a light-emitting control scheme according to the light intensity measured by the light sensor and the control instruction of the body light-emitting control unit and a preset program, and performs power supply control through the body light-emitting power manager.
The positive and negative electrodes of the luminous coating block in the circuit area are positioned outside the machine body, wiring holes are punched in the machine body and are connected with cables through flat head hollow handle nails, the cables are welded in the flat head hollow handle nails, the joints of the flat head hollow handle nails and the cables and the flat head hollow handle nail handles are wrapped with insulating protective sleeves, the lower surface of the nail head and the positive and negative electrodes of the circuit area are coated with conductive adhesive, and the lower surface of the nail head and the positive and negative electrodes of the circuit area are bonded after the flat head hollow handle nails are inserted into the wiring holes; the thickness of the head of the flat-head hollow handle is less than 1mm, and the handle is hollow.
The luminous areas of the luminous coating blocks can be sprayed into any shape, and each luminous area can be sprayed with electroluminescent paint with different colors.
For the manned aircraft, the airframe luminous control unit is integrated on an aircraft flight management system operation platform; for the unmanned aerial vehicle, the body luminous control unit is integrated on the ground station operating platform.
The flight control computer stores power supply control information corresponding to the light-emitting function on, the light-emitting function off and the light-emitting control scheme, and converts the light-emitting control instruction into a power supply control instruction.
The system comprises an autonomous light emitting mode and a manual control light emitting mode, wherein the autonomous light emitting mode determines an autonomous light emitting scheme by comparing a light intensity measured value of a light sensor with a set trigger range of light intensity of each main light emitting scheme; the manual control light-emitting mode is to turn on or off the light-emitting function through the body light-emitting control unit or to control the light-emitting according to a specific scheme.
The electroluminescent coatings of the luminous areas are sprayed on the lower surface and the side surface of the aircraft body, light blue electroluminescent coatings close to the sky in a sunny day are adopted, the flight control computer controls the power supply of the luminous power manager of the aircraft body according to the illumination intensity measured by the light sensor, so that the luminous illumination intensity of each luminous area is the same as the ambient illumination intensity, the contrast ratio of the aircraft and the sky background is greatly reduced, and the visual stealth effect of the aircraft is realized.
The invention has the beneficial effects that: the electroluminescent paint can be applied to various organisms with irregular curved surfaces and shapes; because the luminous zones of the luminous coating blocks can be sprayed into various shapes, and each luminous zone can be sprayed with electroluminescent coatings with different colors, gorgeous and colorful patterns can be formed; because the light-emitting scheme is controllable, the LED lamp can emit no light, continuously emit light, flicker, adjust brightness and the like according to requirements, and the actual effect is richer; the light-emitting control scheme can be switched in real time through the light-emitting control unit of the machine body light-emitting system, so that the use is more flexible. The visual stealth effect of the aircraft on ground observers can be realized, and the visual stealth aircraft can be widely applied to self identification, visual stealth, information transmission, advertising, flight performance and the like.
Drawings
FIG. 1 is a schematic view of an aircraft airframe lighting system of the present invention;
FIG. 2 is a schematic view of an embodiment of the present invention;
FIG. 3 is a schematic layout of an onboard apparatus according to an embodiment of the present invention;
FIG. 4 is a bottom view of the distribution of the electroluminescent coating blocks of the present invention;
FIG. 5 is a side view of a distribution of blocks of a electroluminescent coating in accordance with an embodiment of the present invention;
FIG. 6 is a top view of a distribution of blocks of a electroluminescent coating in accordance with an embodiment of the present invention;
FIG. 7 is a side view of a fuselage luminous coating block assembly according to an embodiment of the present invention;
FIG. 8 is a bottom view of the fuselage luminous coating block assembly of an embodiment of the present invention;
FIG. 9 is a bottom view of the left airfoil luminous coating block assembly in accordance with an embodiment of the present invention;
FIG. 10 is a top view of a left airfoil luminous coating block assembly in accordance with an embodiment of the present invention;
FIG. 11 is a bottom view of the left luminous coating block assembly of the tail wing of the embodiment of the present invention;
FIG. 12 is a top view of a left side of a rear wing of an embodiment of the present invention;
FIG. 13 is a schematic view of a tack of an embodiment of the invention;
FIG. 14 is a schematic illustration of an electrode connection for an electroluminescent coating in accordance with an embodiment of the present invention;
in the figure, 1-fuselage, 2-left wing, 3-right wing, 4-power unit and air bag cabin shell, 5-empennage, 6-left tail support, 7-right tail support, 8-flight control computer, 9-onboard data terminal, 10-aircraft power manager, 11-organism luminous power manager, 12-lithium battery, 13-light sensor, 14-fuselage luminous coating block, 15-left wing luminous coating block, 16-right wing luminous coating block, 17-empennage left luminous coating block, 18-empennage right luminous coating block, 19-fuselage luminous coating block luminous zone, 20-fuselage luminous coating block line connection zone, 21-fuselage luminous coating block positive and negative electrode isolation zone, 22-fuselage luminous coating block positive electrode, 23-a flat-head hollow-handle nail at a positive electrode connection point of a fuselage luminous coating block, 24-a negative electrode of the fuselage luminous coating block, 25-a flat-head hollow-handle nail at a negative electrode connection point of the fuselage luminous coating block, 26-a luminous zone of a left wing luminous coating block, 27-a circuit connection area of the left wing luminous coating block, 28-a positive and negative electrode isolation area of the left wing luminous coating block, 29-a positive electrode of the left wing luminous coating block, 30-a flat-head hollow-handle nail at a positive electrode connection point of the left wing luminous coating block, 31-a negative electrode of the left wing luminous coating block, 32-a negative electrode connection area of the left wing luminous coating block, 33-a luminous coating block of the tail wing, 34-a circuit connection area of the left luminous coating block, 35-a positive and negative electrode isolation area of the left luminous coating block of the, 37-flat-head hollow-handle nail at the positive electrode wiring position of the empennage left luminous coating block, 38-negative electrode of the empennage left luminous coating block, 39-flat-head hollow-handle nail at the negative electrode wiring position of the empennage left luminous coating block, 40-flat-head hollow-handle nail, 41-silver conductive adhesive, 42-positive and negative electrode coatings of the luminous coating block, 43-insulating paint, 44-putty, 45-body, 46-soldering tin, 47-insulating protective sleeve, 48-cable core, 49-cable protective sleeve and 50-organic silicon insulating adhesive.
Detailed Description
The present invention will be further described with reference to the following drawings and examples, which include, but are not limited to, the following examples.
The embodiment of the invention takes a fixed-wing unmanned aerial vehicle for catapult takeoff, parachuting and airbag buffer recovery as an application object, adopts Lumilor brand electroluminescent coating, and implements an aircraft body light-emitting case for flight performance.
Fig. 1 is a schematic view of a lighting system of the present invention, which includes a body lighting control unit, a flight control computer, an onboard data terminal, a lithium battery pack, an aircraft power manager, a body lighting power manager, a light sensor, a lighting coating block, an aircraft body, and a ground data terminal.
The equipment connection mode is as follows: the airframe luminous control unit is integrated in a ground control station and connected with a ground data terminal, the ground data terminal is in radio communication with an airborne data terminal, the airborne data terminal is connected with a flight control computer, an optical sensor is connected with the flight control computer, the flight control computer is connected with an airframe luminous power supply manager, a lithium battery pack is connected with an aircraft power supply manager, the aircraft power supply manager is connected with the airframe luminous power supply manager, the flight control computer, the optical sensor and the airborne data terminal, and the airframe luminous power supply manager is respectively connected with airframe luminous coating blocks, left and right wing luminous coating blocks, and empennage left and right luminous coating blocks.
Fig. 2 is a schematic diagram of an airframe of an embodiment of the present invention, which includes an airframe 1, a left wing 2, a right wing 3, a power unit, an air bag cabin shell 4, a tail wing 5, a left tail support 6, and a right tail support 7, all made of carbon fiber composite materials. Fig. 3 is a schematic layout of an onboard device according to an embodiment of the present invention. Wherein, the flight control computer 8, the airborne data terminal 9, the aircraft power supply manager 10 and the organism luminous power supply manager 11 are arranged on the equipment frame; the lithium battery pack 12 is separately installed inside the machine body; the optical sensor 13 is mounted on the upper part of the body.
The body light-emitting control unit is integrated in the ground control station, and the function window of the body light-emitting control unit comprises a body light-emitting opening button, a closing button, a light-emitting control scheme selection pull-down menu and a scheme execution button.
The light sensor adopts a HuihZD 10AU5 type light intensity sensor.
FIG. 4 is a bottom view of a distribution of blocks of a electroluminescent coating in accordance with an embodiment of the invention, FIG. 5 is a side view of a distribution of blocks of a electroluminescent coating in accordance with an embodiment of the invention, and FIG. 6 is a top view of a distribution of blocks of a electroluminescent coating in accordance with an embodiment of the invention. The luminous coating blocks are symmetrically arranged on the left side and the right side of an aircraft body and comprise a fuselage luminous coating block 14, a left wing luminous coating block 15, a right wing luminous coating block 16, an empennage left luminous coating block 17 and an empennage right luminous coating block 18. The fuselage luminous coating block 14 is made of white-light-emitting paint, the left wing luminous coating block 15 and the right wing luminous coating block 16 are made of green-light-emitting paint, and the empennage left luminous coating block 17 and the empennage right luminous coating block 18 are made of orange-light-emitting paint.
Each luminous coating block comprises a luminous area and a circuit area, and the circuit area comprises a circuit connecting area, an anode and cathode isolating area, an anode and a cathode.
Fig. 7 is a side view of the luminous coating block of the fuselage according to the embodiment of the invention, and fig. 8 is a bottom view of the luminous coating block of the fuselage according to the embodiment of the invention, which includes a luminous zone 19 of the luminous coating block 14 of the fuselage, a circuit connection zone 20 of the luminous coating block 14 of the fuselage, positive and negative electrode isolation zones 21 of the luminous coating block 14 of the fuselage, a positive electrode 22 of the luminous coating block 14 of the fuselage, and a negative electrode 24 of the luminous coating block 14 of the fuselage. The tack hollow nail 23 at the positive electrode wiring of the luminous coating block 14 of the fuselage and the tack hollow nail 25 at the negative electrode wiring of the luminous coating block 14 of the fuselage can be seen in the figure.
Fig. 9 is a bottom view of the left wing luminous coating block in the embodiment of the invention, and fig. 10 is a top view of the left wing luminous coating block in the embodiment of the invention, and the left wing luminous coating block comprises a luminous zone 26 of the left wing luminous coating block 15, a line connection zone 27 of the left wing luminous coating block 15, a positive and negative electrode isolation zone 28 of the left wing luminous coating block 15, a positive electrode 29 of the left wing luminous coating block 15, and a negative electrode 31 of the left wing luminous coating block 15. The tack hollow nail 30 at the positive connection of the left wing luminous coating block 15 and the tack hollow nail 32 at the negative connection of the left wing luminous coating block can be seen in the figure.
Fig. 11 is a bottom view of the left luminous coating block assembly of the tail wing of the embodiment of the invention, and fig. 12 is a top view of the left luminous coating block assembly of the tail wing of the embodiment of the invention, which comprises a left luminous coating block 17 of the tail wing 33, a left luminous coating block 17 of the tail wing 34 of the circuit connection area, a left luminous coating block 17 of the tail wing 35 of positive and negative electrode isolation areas, a left luminous coating block 17 of the tail wing 36 of positive electrode, and a left luminous area 17 of the tail wing 37 of negative electrode. The flat-head hollow handle nail 38 at the positive wiring position of the empennage left luminous coating block 17 and the flat-head hollow handle nail 39 at the negative wiring position of the empennage left luminous coating block 17 can be seen in the figure.
Fig. 13 is a schematic diagram of a flat head hollow handle nail according to an embodiment of the invention, fig. 14 is a schematic diagram of wiring of an electroluminescence coating electrode according to an embodiment of the invention, a wiring hole is punched in a machine body by a positive electrode and a negative electrode of a luminescence coating block, the flat head hollow handle nail 40 is connected with a cable through the flat head hollow handle nail 40, the cable core 48 and the cable protective sleeve 49 are welded in the flat head hollow handle nail 40, the insulation protective sleeve 47 is wrapped outside the nail handle of the flat head hollow handle nail 40, the lower surface of the nail head and the positive electrode and the negative electrode of the luminescence coating block are coated with silver conductive adhesive 41, and the lower surface of the nail head and the positive electrode and the negative electrode of the circuit region; the thickness of the head of the tack hollow handle nail 40 is less than 0.5mm, and the nail handle is hollow. In addition, because the carbon fiber material is conductive, before the electroluminescent coating is sprayed, putty 44 is smeared on the body 45, then insulating paint 43 is sprayed on the area where the luminescent coating block is located, the anode and cathode coatings 42 of the luminescent coating block are sprayed on the insulating paint 43, the hollow handles of the flat head hollow handle nail 40 are filled with soldering tin 46 as much as possible, and after wiring is completed, organic insulating silica gel 50 is smeared on the area where the anode and cathode of the luminescent coating block are located.
The light-emitting control scheme of the embodiment of the invention is added with a flight control program in a module form and is loaded into a flight control computer. Here, 7 emission control schemes are listed: scheme 1, all the luminescent coating blocks do not emit light; scheme 2, all the luminescent coating blocks are normally bright; scheme 3, the brightness of all the luminous coating blocks changes from dark to bright, the period is 1 second, and the cycle is continuous; scheme 4, all the luminous coating blocks flicker in the same period, the luminous time is 0.5 second, and the luminous interval is 0.5 second; in the scheme 5, the luminous coating blocks of the fuselage, the luminous coating blocks of the left wing and the right wing, and the luminous coating blocks of the left wing and the right wing of the empennage sequentially and independently emit light for 0.5 second; and scheme 6, switching to an autonomous light emitting mode.
The working modes of the embodiment of the invention are divided into an autonomous light-emitting mode and a manual control light-emitting mode: (1) an autonomous light emitting mode. The autonomous light-emitting mode is a default light-emitting mode, if the voltage of the light sensor is lower than 0.25V, the corresponding illumination intensity is lower than 100lux, the aircraft starts to execute a light-emitting control scheme 3, otherwise, the light-emitting control scheme 1 is executed, and the flight control computer automatically converts the mode into a manual control light-emitting mode after receiving a ground organism light-emitting control instruction; (2) the light emitting mode is manually manipulated. Ground personnel control the opening and closing of the light-emitting system and the switching control of the working mode and the light-emitting control scheme through the functional window of the light-emitting control unit of the machine body.
The aircraft power supply manager provides a 28V direct-current power supply for the engine body light-emitting power supply manager, and the power supply requirements of all states in the scheme are as follows: when the LED is not lighted, no power is supplied; the constant-brightness or flickering lighting time period requires alternating current of 220V and 800 Hz; the power supply is changed from dark to bright, and the power supply requires 50V-220V range, and 1000Hz alternating current linearly changes along with time.
The specific working example process of the embodiment of the invention is as follows: (1) after the aircraft is subjected to ground self-inspection, an operator clicks a body light-emitting starting button on a body light-emitting control unit functional window, and the flight control computer executes an autonomous light-emitting mode. The flight control computer receives the information of the optical sensor, if the voltage of the optical sensor is lower than 0.25V, the aircraft starts to execute a light-emitting control scheme 3, otherwise, executes a light-emitting control scheme 1 and sends power supply information corresponding to the selected light-emitting control scheme to the organism light-emitting power manager, the organism light-emitting power manager converts the power supply input by the aircraft power manager according to the received power supply information and supplies power to the light-emitting coating blocks, and the light-emitting areas of the light-emitting coating blocks emit light according to the characteristics of the supplied power supply; (2) the aircraft takes off and flies to the height of 300m, and an operator selects the light-emitting control scheme 2 in the functional window of the body light-emitting control unit and clicks an execution button. The ground control station sends an instruction of executing a light emitting control scheme 2 to the aircraft through the ground data terminal, the airborne data link terminal receives the instruction of executing the light emitting control scheme 2 and sends the instruction to the flight control computer, the flight control computer sends power supply information of the light emitting control scheme 2 to the organism light emitting power manager after carrying out data processing, the organism light emitting power manager converts the power supply input by the aircraft power manager according to the power supply information of the light emitting control scheme 2 and supplies power to each light emitting coating block, and the light emitting zone of each light emitting coating block emits light according to the light emitting control scheme 2; (3) thereafter, the body light emission characteristics can be continuously controlled through the body light emission manipulation unit function window.
The above-described embodiments of the invention are merely examples of the invention's application to an aircraft and should not be construed as limiting the claims. The application example itself is modified, for example as follows:
(1) modifying the positions and shapes of the anode and the cathode of the luminescent coating block;
(2) the head and the hollow handle of the flat head hollow handle nail are changed into other shapes;
(3) the body light-emitting manipulation unit is modified to be a separately provided manipulator.
Any modification, equivalent replacement, improvement, split, recombination, etc. within the spirit and principle of the present invention should fall into the protection scope of the claims of the present invention.
Claims (7)
1. The utility model provides an aircraft organism lighting system, mainly includes organism luminous control unit, organism luminous power manager, flight control computer, light sensor, luminous coating piece, its characterized in that: the luminous coating block comprises a luminous region and a circuit region, the luminous region comprises an electroluminescent coating sprayed on a designated part of the aircraft body, the circuit region comprises a circuit connecting region, an anode and cathode isolating region, an anode and a cathode, and the body luminous power manager supplies power to drive the electroluminescent coating to emit light; the body light-emitting control unit is used for carrying out switching control on the on and off of a light-emitting system and a working mode and a light-emitting control scheme; the flight control computer determines a light-emitting control scheme according to the light intensity measured by the light sensor and the control instruction of the body light-emitting control unit and a preset program, and performs power supply control through the body light-emitting power manager.
2. An aircraft airframe lighting system as defined in claim 1, wherein: the positive and negative electrodes of the luminous coating block in the circuit area are positioned outside the machine body, wiring holes are punched in the machine body and are connected with cables through flat head hollow handle nails, the cables are welded in the flat head hollow handle nails, the joints of the flat head hollow handle nails and the cables and the flat head hollow handle nail handles are wrapped with insulating protective sleeves, the lower surface of the nail head and the positive and negative electrodes of the circuit area are coated with conductive adhesive, and the lower surface of the nail head and the positive and negative electrodes of the circuit area are bonded after the flat head hollow handle nails are inserted into the wiring holes; the thickness of the head of the flat-head hollow handle is less than 1mm, and the handle is hollow.
3. An aircraft airframe lighting system as defined in claim 1, wherein: the luminous areas of the luminous coating blocks can be sprayed into any shape, and each luminous area can be sprayed with electroluminescent paint with different colors.
4. An aircraft airframe lighting system as defined in claim 1, wherein: for the manned aircraft, the airframe luminous control unit is integrated on an aircraft flight management system operation platform; for the unmanned aerial vehicle, the body luminous control unit is integrated on the ground station operating platform.
5. An aircraft airframe lighting system as defined in claim 1, wherein: the flight control computer stores power supply control information corresponding to the light-emitting function on, the light-emitting function off and the light-emitting control scheme, and converts the light-emitting control instruction into a power supply control instruction.
6. An aircraft airframe lighting system as defined in claim 1, wherein: the system comprises an autonomous light emitting mode and a manual control light emitting mode, wherein the autonomous light emitting mode determines an autonomous light emitting scheme by comparing a light intensity measured value of a light sensor with a set trigger range of light intensity of each main light emitting scheme; the manual control light-emitting mode is to turn on or off the light-emitting function through the body light-emitting control unit or to control the light-emitting according to a specific scheme.
7. An aircraft airframe lighting system as defined in claim 1, wherein: the electroluminescent coatings of the luminous areas are sprayed on the lower surface and the side surface of the aircraft body, light blue electroluminescent coatings close to the sky in a sunny day are adopted, the flight control computer controls the power supply of the luminous power manager of the aircraft body according to the illumination intensity measured by the light sensor, so that the luminous illumination intensity of each luminous area is the same as the ambient illumination intensity, the contrast ratio of the aircraft and the sky background is greatly reduced, and the visual stealth effect of the aircraft is realized.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911033857.2A CN110844040A (en) | 2019-10-28 | 2019-10-28 | Aircraft body lighting system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911033857.2A CN110844040A (en) | 2019-10-28 | 2019-10-28 | Aircraft body lighting system |
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| CN110844040A true CN110844040A (en) | 2020-02-28 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911033857.2A Pending CN110844040A (en) | 2019-10-28 | 2019-10-28 | Aircraft body lighting system |
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Citations (8)
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|---|---|---|---|---|
| US4864473A (en) * | 1988-03-21 | 1989-09-05 | Asc Incorporated | Electroluminescent dome light for a convertible automobile |
| US20050017130A1 (en) * | 2003-07-25 | 2005-01-27 | Shelly Mark A. | Methods and apparatus for illumination of refueling hoses |
| US20050052880A1 (en) * | 2002-07-22 | 2005-03-10 | Buckingham Thomas Martin | Low light level illumination for rotating objects |
| US20120098455A1 (en) * | 2009-06-22 | 2012-04-26 | Airbus Operations Gmbh | Lighting Device Having A Plurality Of Light Sources |
| US20150037910A1 (en) * | 2012-02-29 | 2015-02-05 | Showa Denko K.K. | Method of manufacturing organic electroluminescent element |
| GB2529442A (en) * | 2014-08-20 | 2016-02-24 | Jaguar Land Rover Ltd | Illumination system |
| US20170365644A1 (en) * | 2017-05-27 | 2017-12-21 | Shanghai Kerun Phosphor Technology Co., Ltd. | Organic silicon electroluminescent display device |
| CN109684174A (en) * | 2018-12-25 | 2019-04-26 | 努比亚技术有限公司 | Mobile terminal outward appearance change method, control device, mobile terminal and storage medium |
-
2019
- 2019-10-28 CN CN201911033857.2A patent/CN110844040A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4864473A (en) * | 1988-03-21 | 1989-09-05 | Asc Incorporated | Electroluminescent dome light for a convertible automobile |
| US20050052880A1 (en) * | 2002-07-22 | 2005-03-10 | Buckingham Thomas Martin | Low light level illumination for rotating objects |
| US20050017130A1 (en) * | 2003-07-25 | 2005-01-27 | Shelly Mark A. | Methods and apparatus for illumination of refueling hoses |
| US20120098455A1 (en) * | 2009-06-22 | 2012-04-26 | Airbus Operations Gmbh | Lighting Device Having A Plurality Of Light Sources |
| US20150037910A1 (en) * | 2012-02-29 | 2015-02-05 | Showa Denko K.K. | Method of manufacturing organic electroluminescent element |
| GB2529442A (en) * | 2014-08-20 | 2016-02-24 | Jaguar Land Rover Ltd | Illumination system |
| US20170365644A1 (en) * | 2017-05-27 | 2017-12-21 | Shanghai Kerun Phosphor Technology Co., Ltd. | Organic silicon electroluminescent display device |
| CN109684174A (en) * | 2018-12-25 | 2019-04-26 | 努比亚技术有限公司 | Mobile terminal outward appearance change method, control device, mobile terminal and storage medium |
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