CN110844040A - An aircraft body lighting system - Google Patents

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

An aircraft body lighting system

technical field

The invention belongs to the technical field of aircraft, and in particular relates to a light-emitting system for an aircraft body.

Background technique

With the development of aerospace technology, aircraft, airships, balloons, satellites and other aircraft have been widely used in civil and military fields. The aircraft body emits light with a specific color, brightness, pattern, or changes in color, brightness, pattern, or flashes regularly, which can be used for self-recognition, visual stealth, information transmission, advertising, air performance, etc.

At present, various types of aircraft mainly emit light through various lamps with a limited number of installations, and the application scope is limited to the identification of the aircraft itself. Some small aircraft also use LED light-emitting lamps, electroluminescent films, fluorescent paints, etc. on the body to emit light. Performance. However, the LED light-emitting light is a point light source. It is installed outside the aircraft to affect the aerodynamic shape of the body. It takes up space when installed inside the aircraft, and requires the body to be transparent. It is inconvenient to use and install on a large scale on the body. The shape of the paint can be paved, but it is difficult to apply to the irregular shape of the aircraft body; the fluorescent paint can be used in a wide range, but its brightness is low, the luminous characteristics are not controllable, and there are many application restrictions. All these factors limit the application of aircraft body lighting.

SUMMARY OF THE INVENTION

In order to overcome the deficiencies of the prior art, the present invention provides an aircraft body lighting system. The invention is convenient to implement, has little influence on aerodynamic shape, can adapt to various irregular body shapes, and can design lighting patterns, adjustable lighting characteristics (brightness, flickering rules, etc.), and switch lighting control schemes in real time.

An aircraft body light-emitting system mainly includes a body light-emitting control unit, a body light-emitting power manager, a flight control computer, a light sensor, and a light-emitting coating block, characterized in that the light-emitting coating block includes a light-emitting area and a circuit area, The light-emitting area includes the electroluminescent coating sprayed on the designated parts of the aircraft body, and the circuit area includes the circuit connection area, the positive and negative isolation area, the positive electrode and the negative electrode, which are powered by the body light-emitting power manager to drive the electroluminescence. The coating emits light; the light-emitting control unit of the body performs the opening and closing of the light-emitting system, as well as the switching control of the working mode and the light-emitting control scheme; the flight control computer is based on the light intensity measured by the light sensor and the control instructions of the light-emitting control unit of the body, according to the preset. The program determines the lighting control scheme, and controls the power supply through the body lighting power manager.

The positive and negative electrodes of the circuit area of the luminescent coating block are located outside the body, and wiring holes are drilled into the body to connect with the cable through the flat-head hollow handle nail, the flat-head hollow handle nail is welded with the cable in the hollow handle, and the flat-head hollow handle nail is connected with the cable. The lower surface of the nail head and the positive and negative electrodes of the circuit area are coated with conductive glue. After the flat-head hollow shank nail is inserted into the wiring hole, the lower surface of the nail head and the positive and negative electrodes of the circuit area are bonded. ; The thickness of the flat head hollow handle nail is less than 1mm, and the nail handle is hollow.

The light-emitting area of the light-emitting coating block can be sprayed into any shape, and each light-emitting area can be sprayed with electroluminescent paint of different colors.

For manned aircraft, the light-emitting control unit of the body is integrated into the operation platform of the aircraft flight management system; for the unmanned aircraft, the light-emitting control unit of the body is integrated into the operation platform of the ground station.

The flight control computer stores the 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 instructions into power-supply control instructions.

The system includes two modes of self-illumination and manual light-emitting. The self-illumination mode determines the self-illumination scheme by comparing the measured value of the light intensity of the light sensor with the set trigger range of the illumination intensity of the main light-emitting scheme; the self-illumination scheme is determined; The manual control light-emitting mode is to turn on or off the light-emitting function through the light-emitting control unit of the body or perform light-emitting control according to a specific scheme.

The electroluminescent coating in the light-emitting area is sprayed on the lower surface and side of the aircraft body, and a light blue electroluminescent coating similar to the sunny sky is used. The flight control computer supplies the light-emitting power to the body according to the light intensity measured by the light sensor The manager controls the power supply, so that the luminous intensity of each light-emitting area is the same as the ambient light intensity, which greatly reduces the contrast between the aircraft and the sky background, and realizes the visual stealth effect of the aircraft.

The beneficial effects of the present invention are: because the electroluminescent paint is used, it can be applied to various curved surfaces and bodies with irregular shapes; the light-emitting area of the light-emitting coating block can be sprayed into various shapes, and each light-emitting area can be sprayed differently Colored electroluminescent coatings can form colorful patterns; because the lighting scheme is controllable, it can be non-emitting, continuous lighting, flickering, and brightness adjustment according to the requirements, and the actual effect is more abundant; because the lighting control scheme can be controlled by the body lighting system. The lighting control unit is switched in real time, making it more flexible to use. The invention can realize the visual stealth effect of the aircraft to ground observers, and can be widely used in self-recognition, visual stealth, information transmission, advertising, air performance and the like.

Description of drawings

1 is a schematic diagram of a light-emitting system of an aircraft body according to the present invention;

2 is a schematic diagram of the body of the embodiment of the present invention;

FIG. 3 is a schematic diagram of the arrangement of airborne equipment according to an embodiment of the present invention;

4 is a bottom view of the distribution of the light-emitting coating blocks of the body according to the embodiment of the present invention;

5 is a side view of the distribution of the light-emitting coating blocks of the body according to the embodiment of the present invention;

6 is a top view of the distribution of the light-emitting coating blocks of the body according to the embodiment of the present invention;

7 is a side view of the composition of the light-emitting coating block of the fuselage according to the embodiment of the present invention;

FIG. 8 is a bottom view of the composition of the light-emitting coating block of the fuselage according to the embodiment of the present invention;

9 is a bottom view of the composition of the left wing luminescent coating block according to the embodiment of the present invention;

10 is a top view of the composition of the luminescent coating block of the left wing according to the embodiment of the present invention;

11 is a bottom view of the composition of the left luminescent coating block of the tail wing according to the embodiment of the present invention;

12 is a top view of the composition of the left luminescent coating block of the tail wing according to the embodiment of the present invention;

13 is a schematic diagram of a flat-head hollow handle nail according to an embodiment of the present invention;

FIG. 14 is a schematic diagram of the electrode wiring of the electroluminescent coating according to the embodiment of the present invention;

In the picture, 1-fuselage, 2-left wing, 3-right wing, 4-power unit and airbag housing, 5-tail, 6-left tail, 7-right tail, 8-flight control Computer, 9-airborne data terminal, 10-aircraft power manager, 11-body light-emitting power manager, 12-lithium battery pack, 13-light sensor, 14-body light-emitting coating block, 15-left wing light-emitting Coating block, 16-right wing luminous coating block, 17- tail fin left luminous coating block, 18- tail fin right luminous coating block, 19- fuselage luminous coating block luminous area, 20- fuselage luminous coating Block circuit connection area, 21-body light-emitting coating block positive and negative isolation area, 22-body light-emitting coating block positive electrode, 23-body light-emitting coating block positive terminal flat head empty handle nail, 24-body light-emitting Negative electrode of coating block, 25- Flat head empty handle nail at the negative terminal of fuselage light-emitting coating block, 26- Light-emitting area of left-wing light-emitting coating block, 27- Line connection area of left-wing light-emitting coating block, 28- Left machine Positive and negative isolation area of wing light-emitting coating block, 29-left wing light-emitting coating block positive electrode, 30-left wing light-emitting coating block positive terminal flat head empty handle nail, 31-left wing light-emitting coating block negative electrode, 32- Flat head empty handle nail at the negative terminal of the left wing light-emitting coating block, 33- tail light coating block left light coating block, 34- tail light coating block line connection area, 35- tail light coating block left Positive and negative separation area, 36- tail wing left light-emitting coating block positive electrode, 37- tail wing left light-emitting coating block positive terminal flat head empty handle nail, 38- tail wing left light-emitting coating block negative electrode, 39- tail wing left light-emitting coating block Flat head empty handle nail at the negative terminal, 40- flat head empty handle nail, 41- silver conductive glue, 42- luminous coating block positive and negative electrode coating, 43- insulating paint, 44- putty, 45- body, 46- solder, 47- Insulation protection sleeve, 48- Cable core, 49- Cable protection sleeve, 50- Silicone insulating glue.

Detailed ways

The present invention will be further described below with reference to the accompanying drawings and embodiments, and the present invention includes but is not limited to the following embodiments.

The embodiment of the present invention takes a fixed-wing unmanned aerial vehicle for ejection takeoff, parachute landing, and airbag buffer recovery as an application object, and uses Lumilor brand electroluminescent paint to implement a case of aircraft body lighting for air performances.

1 is a schematic diagram of a light-emitting system of the present invention, including a body light-emitting control unit, a flight control computer, an airborne data terminal, a lithium battery pack, an aircraft power manager, a body light-emitting power manager, a light sensor, a light-emitting coating block, an aircraft body, ground data terminal.

The connection method of the equipment is as follows: the light-emitting control unit of the body is integrated into the ground control station and connected to the ground data terminal. The ground data terminal and the airborne data terminal communicate by radio, the airborne data terminal is connected to the flight control computer, and the light sensor is connected to the flight control computer. , the flight control computer is connected to the body light-emitting power manager, the lithium battery pack is connected to the aircraft power manager, the aircraft power manager is connected to the body light-emitting power manager, the flight control computer, the light sensor, and the airborne data terminal. The body light-emitting power management The device is connected with the fuselage light-emitting coating block, the left and right wing light-emitting coating blocks, and the left and right light-emitting coating blocks of the tail wing respectively.

2 is a schematic diagram of the body of the embodiment of the present invention, including a fuselage 1, a left wing 2, a right wing 3, a power unit and an airbag housing 4, a tail wing 5, a left tail support 6, and a right tail support 7, all of which are made of carbon fiber. composite material. FIG. 3 is a schematic diagram of the arrangement of airborne equipment according to an embodiment of the present invention. Among them, the flight control computer 8, the onboard data terminal 9, the aircraft power manager 10, and the body light-emitting power manager 11 are installed on the equipment rack; the lithium battery pack 12 is separately installed inside the fuselage; the light sensor 13 is installed on the upper part of the fuselage .

The body light-emitting control unit is integrated in the ground control station, and its function window includes a body light-emitting on button, a close button, a light-emitting control scheme selection drop-down menu, and a scheme execution button.

The light sensor adopts Nenghui NHZD10AU5 illuminance sensor.

4 is a bottom view of the distribution of the light-emitting coating blocks of the body according to the embodiment of the present invention, FIG. 5 is a side view of the distribution of the light-emitting coating blocks of the body of the embodiment of the present invention, and FIG. 6 is a top view of the distribution of the light-emitting coating blocks of the body of the embodiment of the present invention. The luminescent coating blocks are symmetrically arranged on the left and right sides of the aircraft body, including the fuselage luminescent coating block 14, the left wing luminescent coating block 15, the right wing luminescent coating block 16, the tail fin left luminescent coating block 17 and the tail fin right luminous coating block 17 Coating block 18. Among them, the fuselage luminescent coating block 14 adopts white luminescent paint, the left wing luminescent coating block 15 and the right wing luminescent coating block 16 use green luminescent paint, the tail fin left luminescent coating block 17 and the tail right luminous coating Layer block 18 is painted with an orange glow.

Each light-emitting coating block includes a light-emitting area and a circuit area, and the circuit area includes a line connection area, a positive and negative electrode isolation area, a positive electrode and a negative electrode.

FIG. 7 is a side view of the composition of the light-emitting coating block of the body according to the embodiment of the present invention, and FIG. 8 is a bottom view of the composition of the light-emitting coating block of the body according to the embodiment of the present invention, including the light-emitting area 19 of the light-emitting coating block 14 of the body, and the light-emitting coating block of the body of the embodiment of the present invention. Layer block 14 line connection area 20 , body luminescent coating block 14 positive and negative electrode isolation area 21 , body luminescent coating block 14 positive electrode 22 , body luminescent coating block 14 negative electrode 24 . In the figure, it can be seen that the flat head empty handle nail 23 at the positive terminal of the luminous coating block 14 of the body, and the flat head empty handle nail 25 at the negative terminal of the body luminescent coating block 14 .

9 is a bottom view of the composition of the luminescent coating block of the left wing according to the embodiment of the present invention, and FIG. 10 is a top view of the composition of the luminescent coating block of the left wing according to the embodiment of the present invention, including the luminous area 26 of the luminescent coating block 15 of the left wing, The wing luminescent coating block 15 has a line connection area 27 , the left wing luminescent coating block 15 has a positive and negative electrode isolation area 28 , the left wing luminescent coating block 15 has a positive electrode 29 , and the left wing luminescent coating block 15 has a negative electrode 31 . In the figure, we can see the flat head empty handle nail 30 at the positive terminal of the left wing luminescent coating block 15, and the flat head empty handle nail 32 at the negative terminal of the left wing luminous coating block.

Fig. 11 is a bottom view of the composition of the left luminous coating block of the tail fin according to the embodiment of the present invention, and Fig. 12 is a top view of the composition of the left luminous coating block of the empennage according to the embodiment of the present invention, including the luminous coating block 17 of the left empennage coating block 33, and the left luminous coating block of the tail fin. The coating block 17 has a line connection area 34 , the tail left light emitting coating block 17 has a positive and negative electrode isolation area 35 , the tail left light emitting coating block 17 has a positive electrode 36 , and the tail left light emitting area 17 has a negative electrode 37 . In the figure, it can be seen that the flat head empty handle nail 38 at the positive terminal of the left luminous coating block 17 of the tail wing, and the flat head empty handle nail 39 at the negative terminal of the tail fin left luminous coating block 17.

Fig. 13 is a schematic diagram of a flat-headed hollow handle nail according to an embodiment of the present invention, and Fig. 14 is a schematic diagram of the wiring of the electroluminescent coating electrode according to an embodiment of the present invention. 40 is connected to the cable, the flat head hollow handle nail 40 is welded with the cable core 48 in the hollow handle, the cable core 48 and the cable protective sleeve 49 at the connection between the flat head hollow handle nail and the cable, and the flat head hollow handle nail 40 The nail handle is wrapped with an insulating protective sleeve 47 , the lower surface of the nail head and the positive and negative electrodes of the luminous coating block are coated with silver conductive glue 41, and the flat head hollow handle nail 40 is inserted into the wiring hole to complete the bonding between the lower surface of the nail head and the positive and negative electrodes of the circuit area; the flat head hollow handle nail 40 nails The thickness of the head is less than 0.5mm, and the shank is hollow. In addition, because the carbon fiber material is conductive, before spraying the electroluminescent paint, putty 44 is applied to the body 45, and then insulating paint 43 is sprayed on the area where the luminescent coating block is located, and the positive and negative electrode coatings 42 of the luminescent coating block are sprayed on the insulating paint 43. , the solder 46 should be filled as much as possible with the empty handle of the flat-head empty handle nail 40. After the wiring is completed, apply organic insulating silica gel 50 to the area where the positive and negative electrodes of the luminescent coating block are located.

The lighting control scheme of the embodiment of the present invention is added to the flight control program in the form of modules and loaded into the flight control computer. Here are 7 luminous control schemes: scheme 1, all luminescent coating blocks do not emit light; scheme 2, all luminescent coating blocks are always on; scheme 3, the brightness of all luminescent coating blocks changes from dark to bright, with a cycle of 1 second, Continuous cycle; Option 4, all luminescent coating blocks flash in the same period, emitting time 0.5 seconds, emitting interval 0.5 seconds; Option 5, luminescent coating blocks on the fuselage, luminescent coating blocks on the left and right wings, and luminescent coating blocks on the left and right tails in sequence Light up alone, with a duration of 0.5 seconds; scheme 6, switch to self-illumination mode.

The working modes of the embodiments of the present invention are divided into two types: autonomous lighting mode and manual manipulation lighting mode: (1) Autonomous lighting mode. The autonomous lighting mode is the default lighting mode. If the voltage of the light sensor is lower than 0.25V and the corresponding light intensity is lower than 100lux, the aircraft starts to execute the lighting control scheme 3, otherwise, the lighting control scheme 1 is executed, and the flight control computer receives the ground body lighting control command After that, it is automatically converted to the manual-operated light-emitting mode; (2) the manual-operated light-emitting mode. The ground personnel can turn on and off the lighting system, and switch the working mode and lighting control scheme through the function window of the light-emitting control unit of the body.

The aircraft power manager in the embodiment of the present invention provides 28V DC power for the light-emitting power manager of the body. The power supply requirements for each state in the scheme are as follows: when no light is emitted, no power is supplied; the constant light or flashing light time period requires 220V, 800Hz AC power; The brightening power supply requires alternating current in the range of 50V ~ 220V and 1000Hz linearly changing with time.

The specific working example process of the embodiment of the present invention is as follows: (1) After the aircraft self-checks on the ground, the operator clicks the body light-on button in the body light-emitting control unit function window, and the flight control computer executes the autonomous light-emitting mode. The flight control computer receives the light sensor information. If the light sensor voltage is lower than 0.25V, the aircraft starts to execute the lighting control scheme 3. Otherwise, it executes the lighting control scheme 1, and sends the power supply information corresponding to the selected lighting control scheme to the body lighting power manager. , the body light-emitting power manager converts the power input from the aircraft power manager according to the received power supply information, and supplies power to each light-emitting coating block, and the light-emitting area of each light-emitting coating block emits light according to the characteristics of the power supply; (2) The aircraft takes off and flies to a height of 300m. The operator selects light-emitting control scheme 2 in the function window of the light-emitting control unit of the body, and clicks the execution button. The ground control station sends the "execute light-emitting control plan 2" command to the aircraft through the ground data terminal, and the airborne data link terminal receives the "execute light-emitting control plan 2" command and sends it to the flight control computer. After data processing, the flight control computer sends the data to the aircraft. The airframe light-emitting power manager sends the power supply information of "light-emitting control scheme 2", and the body light-emitting power manager converts the power input from the aircraft power manager according to the power supply information of "light-emitting control scheme 2", and sends the power supply to each light-emitting coating block. Power is supplied, and the light-emitting area of each light-emitting coating block emits light according to the "light-emitting control scheme 2"; (3) After that, the light-emitting characteristics of the body can be controlled through the function window of the light-emitting control unit of the body.

The above-mentioned embodiments of the present invention are only examples of the application of the present invention to an aircraft, and should not be considered as limitations on the claims of the present invention. Modify the application instance itself, for example:

(1) Modification of the position and shape of the positive and negative electrodes of the luminescent coating block;

(2) The nail head and hollow handle of the flat-head hollow-handled nail are changed to other shapes;

(3) The body light-emitting manipulation unit is modified to a manipulator provided separately.

Any modification, equivalent replacement, improvement, disassembly, reorganization, etc. made within the spirit and principle of the present invention shall fall within 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.

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