CN115585412A - An integrated aircraft refueling lamp - Google Patents

Abstract

The application provides an integrated aircraft refueling lamp, which belongs to the technical field of lighting design for aircraft aerial refueling systems, and specifically includes a housing assembly, a light source assembly, a drive assembly, and a light source regulator. The housing assembly includes a housing and a The first cavity and the second cavity, the light source assembly is arranged in the first cavity, the driving assembly and the light source regulator are arranged in the second cavity, the light source assembly, the driving assembly and the light source regulator are connected in sequence, and the light source assembly is provided with an oil receiving In probe lighting mode and taper sleeve flood lighting mode, the driving component is used to divide the voltage and control the constant current, and the light source component is used to stabilize the input voltage when changing the light intensity. Through the processing scheme of the present application, the airborne equipment has the advantages of light weight, integration, low cost and simple control.

Description

An integrated aircraft refueling lamp

technical field

The present application relates to the technical field of lighting design for an aircraft aerial refueling system, in particular to an integrated aircraft refueling lamp.

Background technique

With the need for war preparations, the range of aircraft needs to be expanded. Since the debut of the first aerial refueling aircraft in the United States in 1923, aerial refueling technology has developed unprecedentedly. When it is necessary to refuel in the air at night, the refueling lamp in the air is extremely urgent and necessary. When the aircraft is at the docking position for refueling in the air, the drogue floodlight of the aircraft is used to illuminate the conical tube 15m away from the top of the refueling plug to ensure that the driver of the refueling aircraft can directly see the refueling under the light. The drogue sleeve is used for refueling and docking work; the oil receiving probe lamp is used to illuminate the oil receiving probe nozzle and the drogue sleeve during the final engagement of the oil receiving probe nozzle and the drogue sleeve to ensure that the driver of the oil receiving machine The probe tube under the illumination of the oil probe lamp can be directly seen. In the past, two types of refueling lamps were required for refueling aircraft, namely, the refueling plug lighting and the refueling area lighting, which were used to illuminate the refueling plug and the refueling area, including illuminating the drogue sleeve, but the two refueling lamps were for aircraft It increases the weight, takes up too much space and installation position, and increases the control complexity, cost expenditure, and reduces the reliability. Therefore, it is extremely necessary to propose a fuel lamp with two functions simultaneously.

Contents of the invention

In view of this, the embodiment of the present application provides an integrated aircraft refueling lamp, which at least partially solves the problems of heavy aircraft weight and complicated control caused by the separate design of the refueling plug lighting lamp and the refueling area lighting lamp in the prior art.

The embodiment of the present application provides an integrated aircraft refueling lamp, which is installed on the telescopic bracket of the refueling probe lamp of the refueling machine. The integrated aircraft refueling lamp includes a housing assembly, a light source assembly, a drive assembly, and a light source regulator. The housing The body assembly includes a housing and a first cavity and a second cavity disposed in the housing, the light source assembly is disposed in the first cavity, the drive assembly and the light source regulator are disposed in the In the second cavity, the light source assembly, the drive assembly and the light source regulator are connected in sequence, the light source assembly is provided with an oil probe lighting mode and a drogue flood lighting mode, and the drive assembly is used to divide The voltage and control current are constant, and the light source component is used to stabilize the input voltage when the light intensity is changed.

According to a specific implementation of the embodiment of the present application, the light source assembly includes a glass screen, a TIR lens, and a light source printed board connected in sequence, the surface of the glass screen is coated with an infrared cut-off film, and the middle of the light source printed board The region is provided with taper sleeve flood lighting lamps, and a plurality of oil receiving probe lighting lamps are arranged around the light source printed board, and a concealed mode light source is arranged between adjacent oil receiving probe lighting lamps. The TIR lens includes a drogue floodlight lens arranged opposite to the drogue floodlight and an oil illuminated lens arranged opposite to the oil probe light.

According to a specific implementation of the embodiment of the present application, the surface of the oil-received lighting lens is provided with a bead surface, and the bead surface is used to ensure the uniformity of light distribution; the surface of the tapered sleeve flood lens is provided with a prism, the Prisms are used to ensure the deflection angle of light.

According to a specific implementation manner of the embodiment of the present application, the edge of the glass screen is provided with an annular groove, and a sealing ring is provided in the groove.

According to a specific implementation manner of the embodiment of the present application, the housing includes a bottom surface, a surface A on the top, and surfaces B, C and D on the sides, and the C surface and the D surface are arranged opposite to each other; The A surface is a quadrilateral in space, the B surface and the C surface are perpendicular to the bottom surface, and the bottom surface is used as a reference zero surface, and the line-plane angle α between the left side of the A surface and the bottom surface is 18° ~20°, the line-plane angle β between the right side of the A surface and the bottom surface is 8°-10°.

According to a specific implementation of the embodiment of the present application, the C surface, the D surface, and the bottom surface all have cooling fins, and the cooling fins on the C surface, the D surface cooling fins, and the bottom surface The surfaces of the heat dissipation grooves formed by the heat dissipation fins are all parallel to the A surface.

According to a specific implementation of the embodiment of the present application, a front end cover is provided on the A surface, the front end cover is located on the first cavity, and the front end cover is conformal to the A surface; the first The second cavity is provided with a rear end cover.

According to a specific implementation of the embodiment of the present application, the drive component and the light source regulator convert the external input voltage into a PWM control signal with a constant frequency and a variable duty cycle through a pulse width modulation circuit, and by adjusting the duty cycle of the PWM The duty ratio adjusts the change of output current.

According to a specific implementation manner of the embodiment of the present application, the light source assembly further includes a fixing plate, and the TIR lens is installed in the first cavity through the fixing plate.

According to a specific implementation manner of the embodiment of the present application, both the drogue flood lighting and the oil receiving probe lighting are configured as LED lights.

Beneficial effect

The integrated aircraft refueling lamp in the embodiment of this application integrates the functions of the aircraft drogue floodlight and the refueling probe lamp to meet the requirements of light weight, integration, low cost and simple control of airborne equipment; the integrated LED On the basis of the traditional stand-alone oil receiving plug lighting and refueling area lighting, the aircraft refueling lamp adopts the integrated design of the oil receiving probe lighting and the cone sleeve flood lighting source, through the spatial configuration The method makes the structure of the shell assembly compact, meets the performance requirements of the refueling lamp, reduces the load of the aircraft, and simplifies the control mode.

Use a light source regulator to convert the external input voltage into a PWM control signal with a constant frequency and a variable duty cycle through a pulse width modulation circuit, and adjust the output current by adjusting the duty cycle of the PWM to adjust the current input by the driver and adjust the LED chip. Finally, the pilot can adjust the brightness of the LED aircraft refueling light by turning the knob on the control panel on the aircraft, so that the light can meet the visual needs of the pilot in different situations and optimize the human-computer interaction.

Description of drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following will briefly introduce the accompanying drawings that need to be used in the embodiments. Obviously, the accompanying drawings in the following description are only some embodiments of the present application. Those of ordinary skill in the art can also obtain other drawings based on these drawings without any creative effort.

Fig. 1 is a schematic structural view of an integrated aircraft refueling lamp according to an embodiment of the present invention;

2 is a schematic diagram of a light source assembly of an integrated aircraft refueling lamp according to an embodiment of the present invention;

Fig. 3 is an isometric view of a housing assembly of an integrated aircraft refueling lamp according to an embodiment of the present invention;

Fig. 4 is a schematic diagram of the irradiation light cone of the integrated aircraft refueling lamp according to an embodiment of the present invention;

Fig. 5 is a schematic diagram of TIR lens beam irradiation of an integrated aircraft refueling lamp according to an embodiment of the present invention.

In the figure: 1, housing assembly; 1-1, housing; 1-2, front end cover; 1-3, rear end cover; 2, light source assembly; 2-1, glass screen; 2-2, sealing ring; 2-3. Fixed plate; 2-4. TIR lens; 2-5. Light source printed board; 3. Drive component; 4. Light source regulator.

detailed description

Embodiments of the present application will be described in detail below in conjunction with the accompanying drawings.

Embodiments of the present application are described below through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Apparently, the described embodiments are only some of the embodiments of this application, not all of them. The present application can also be implemented or applied through other different specific implementation modes, and various modifications or changes can be made to the details in this specification based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the case of no conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application.

It is noted that the following describes various aspects of the embodiments that are within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is illustrative only. Based on the present application one skilled in the art should appreciate that an aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, any number of the aspects set forth herein can be used to implement an apparatus and/or practice a method. In addition, such an apparatus may be implemented and/or such a method practiced using other structure and/or functionality than one or more of the aspects set forth herein.

It should also be noted that the diagrams provided in the following embodiments are only schematically illustrating the basic idea of the application, and only the components related to the application are shown in the drawings rather than the number, shape and number of components in actual implementation. Dimensional drawing, the type, quantity and proportion of each component can be changed arbitrarily during actual implementation, and the component layout type may also be more complicated.

Additionally, in the following description, specific details are provided to facilitate a thorough understanding of examples. However, it will be understood by those skilled in the art that the described aspects may be practiced without these specific details.

The embodiment of the present application provides an integrated aircraft refueling lamp, which is installed on the telescopic bracket of the refueling probe lamp of the refueling machine. GJB2020A-2012 requires the design of the lighting standard for the oil receiver lamp of the oil receiver, which will be described in detail below with reference to Figures 1 to 5.

In this embodiment, the integrated aircraft refueling lamp includes a housing assembly 1, a light source assembly 2, a drive assembly 3 and a light source regulator 4, and the housing assembly 1 includes a housing 1-1 and a The first cavity and the second cavity, the light source assembly 2 is arranged in the first cavity, the driving assembly 3 and the light source regulator 4 are arranged in the second cavity, the light source assembly 2, the driving assembly 3 and the light source regulator 4 are connected in sequence, The light source assembly 2 is used to stabilize the input voltage when the light intensity is changed, and the drive assembly 3 is used to divide the voltage and control the constant current. Adjust the light to meet the visual needs of pilots in different situations.

According to a specific implementation of the embodiment of the present application, the light source assembly 2 includes a glass screen 2-1, a TIR lens 2-4, and a light source printed board 2-5 connected in sequence, and the edge of the glass screen 2-1 is provided with an annular concave Groove, a sealing ring 2-2 is arranged in the groove, in order to ensure the tightness, a sealing ring 2-2 is respectively arranged on both sides of the glass screen 2-1, and the surface of the glass screen 2-1 is coated with an infrared cut-off film.

The middle area of the light source printed board 2-5 is provided with a tapered sleeve floodlight, and the surroundings of the light source printed board 2-5 are provided with a plurality of oil receiving probe lighting lamps, and between adjacent oil receiving probe lighting lamps Has a stealth mode light source. The TIR lens 2-4 is installed on the boss inside the first cavity through the fixed plate 2-3, and the TIR lens 2-4 includes the tapered sleeve floodlight lens arranged opposite to the tapered sleeve floodlight and the oil receiving probe tube illumination The oil-receiving lighting lens set opposite to the lamp, TIR lens 2-4 performs scientific secondary light distribution on the light emitted by the oil-receiving probe lighting lamp and the cone sleeve flood lighting lamp, so as to achieve the required light intensity and irradiation effect.

Further, the surface of the oil-lighting lens is provided with a bead surface, and the bead surface is used to ensure the uniformity of light distribution; the surface of the tapered sleeve flood lens is provided with a prism, and the prism is used to ensure the deflection angle of the light.

In one embodiment, the drogue sleeve flood lighting is set as one LED lamp for drogue sleeve flood lighting in friendly mode, and one LED light for drogue sleeve flood lighting in friendly mode passes through TIR lens 2-4 and the prism above After refraction, the secondary light distribution becomes a regular light beam refracted at a certain angle to illuminate the drogue sleeve of the aircraft. The lighting of the oil probe tube is set to 4 LED lights illuminated by the oil probe tube in the friendly mode, and the 4 LED lights illuminated by the oil probe tube in the friendly mode pass through the TIR lens 2-4 and the bead surface on the secondary light distribution After that, it becomes a regular beam with uniform spot to illuminate the oil receiving probe of the aircraft.

In a specific embodiment, in order to ensure the lighting effect, the housing assembly 1 is designed, and the housing 1 in the housing assembly 1 includes a bottom surface, an A surface on the top, and a B surface, a C surface and a D surface on the side. , the C surface and the D surface are arranged oppositely, and the opposite side of the B surface is the area where the second cavity is located. It can be seen from the figure that the A surface, the B surface, the C surface and the D surface enclose the area where the first cavity is located. Surface A is a quadrilateral in space, surfaces B and C are perpendicular to the installation bottom surface, and the bottom surface is used as the reference zero surface. The line-plane angle α between the left side of A surface and the bottom surface is 18°～20°, and the line surface angle between the right side of A surface and the bottom surface Angle β is 8°～10°. Adjusting the α and β angles can change the illumination effect of the refueling lamp and the glare degree of different working conditions. When α tends to 20° and β angle tends to 8°, the irradiation effect of the irradiated object is better, and it can also effectively Avoid glare to the pilot due to the reflected light after the light hits the metal surface of the aircraft; the distance between the intersection of the left and right sides of the A surface and the bottom surface determines the distance between the light emitting surface of the refueling lamp and the illuminated object, and the light cone formed within the two angle ranges It can not only meet the actual use requirements, but also avoid glare. The A surface formed in this way ensures the performance and irradiation requirements of the integrated aircraft refueling lamp, and conforms to ergonomics.

Therefore, in a preferred embodiment, the A surface is a space quadrilateral, and the dihedral angle formed by the A surface and the C surface is 96°18', and the dihedral angle formed by the A surface and the B surface is 108°48'; The bottom surface is the reference zero surface, the line-plane angle between the left side of surface A and the bottom surface is 20°, and the line-plane angle between the right side of A surface and the bottom surface is 8°. The A surface formed by this ensures the performance of the integrated aircraft refueling lamp. Require.

In this embodiment, through the inclination of the surface angles of the A surface, the B surface, and the C surface on the housing 1-1, and the inclination design of the two sides of the A surface and the bottom surface, the irradiation range of the light can be irradiated to the refueling area of the aircraft; as shown in the figure As shown in 3, the dark large light cone represents the theoretical light cone A required by the standard, the light large light cone represents the designed light cone main beam B, and the light small light cone represents the designed light cone secondary beam C. The main beam B can illuminate the conical tube 15m away from the top of the oil receiving plug, that is, it has achieved the function of the aircraft drogue floodlight, and the secondary beam C can illuminate the oil receiving probe during the final engagement of the oil receiving probe nozzle and the drogue sleeve. The nozzle of the probe tube and the taper sleeve are illuminated to illuminate the oil receiving probe tube, which has reached the function of the oil receiving probe lamp.

Further, there are cooling fins on the C surface, D surface and the bottom surface, and the heat dissipation grooves formed by the C surface cooling fins, the D surface cooling fins and the bottom surface cooling fins are all parallel to the A surface, which can ensure the largest heat dissipation area and heat dissipation. Best results.

In one embodiment, the housing assembly 1 further includes a front cover 1-2, the front cover 1-2 is located on the first cavity and the front cover 1-2 conforms to the surface A, and the second cavity is provided with a rear end Cover 1-3.

Specifically, the front end cover 1-2 is mounted on the first cavity of the casing 1-1 by screws, and two corners of the second cavity are provided with protrusions, and the protrusions limit the position of the rear end cover 1-3.

In one embodiment, the driving component 3 and the light source regulator 4 convert the external input voltage into a PWM control signal with a constant frequency and a variable duty ratio through a pulse width modulation circuit, and adjust the change of the output current by adjusting the duty ratio of the PWM, Finally, the pilot can adjust the brightness of the LED aircraft refueling lamp by turning the knob on the control panel on the aircraft.

Specifically, when an aircraft refuels in the air at night, the pilot needs to find the relative position of the oil receiving probe and the oil delivery port in the area illuminated by the refueling lamp. By operating the knob on the aircraft control panel, the naked eye can better understand the emitted light. Adaptation, pilots can complete aerial refueling tasks more accurately. One end of the light source regulator 4 is connected to an external socket, and the other end is connected to the drive assembly 3 , and the drive assembly 3 is connected to the light source assembly 2 . When the light intensity does not meet the needs of the pilot, the pilot controls the input voltage of the light source regulator 4 by adjusting the knob on the control panel, and the light source regulator 4 converts the changed input voltage into a PWM control signal with a duty cycle change, and then Adjust the input current of the driving component 3, and at the same time, stabilize the voltage and current to ensure the stability of the light source of the light source component 2. The finally changed current is input into the light source component 2, and the light intensity is adjusted with the change of the current to meet the requirements of the pilot. light intensity requirements.

The aircraft refueling lamp of the present application is an auxiliary equipment of the aircraft external lighting system, and its function is to enable the pilot to see the oil receiving probe tube illuminated by the floodlight and to be able to Light the nozzle and taper sleeve of the oil receiving probe, illuminate the oil receiving probe, and install it on the telescopic bracket of the oil receiving probe lamp. The working principle is that after the 28VDC is turned on, the driver component stabilizes the input voltage, and the light emitted by the LED chip (cone sleeve floodlight and oil probe light) is refracted by the TIR lens to obtain the required beam.

The above is only a specific embodiment of the application, but the scope of protection of the application is not limited thereto. Any person familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the application. All should be covered within the scope of protection of this application. Therefore, the protection scope of the present application should be based on the protection scope of the claims.

Claims (10)

1. The utility model provides an integrated form aircraft fueling lamp, installs on receiving oil machine oil probe lamp telescopic bracket, a serial communication port, integrated form aircraft fueling lamp includes casing subassembly, light source subassembly, drive assembly and light source regulator, the casing subassembly includes the casing and sets up first cavity and second cavity in the casing, the light source subassembly set up in the first cavity, drive assembly with the light source regulator set up in the second cavity, the light source subassembly drive assembly with the light source regulator connects gradually, the light source subassembly is equipped with oil probe lighting mode and taper sleeve floodlighting mode, drive assembly is used for partial pressure and control current invariant, the light source subassembly is used for stabilizing input voltage when changing the light intensity.

2. The integrated aircraft fuel filling lamp of claim 1, wherein the light source assembly comprises a glass screen, a TIR lens and a light source printed board which are connected in sequence, the surface of the glass screen is coated with an infrared cut-off film, the middle area of the light source printed board is provided with a taper sleeve floodlight lamp, the periphery of the light source printed board is provided with a plurality of oil-receiving probe lamps, a hidden mode light source is arranged between the adjacent oil-receiving probe lamps, and the TIR lens comprises a taper sleeve floodlight lens arranged opposite to the taper sleeve floodlight lamp and an oil-receiving lighting lens arranged opposite to the oil-receiving probe lamps.

3. The integrated aircraft refueling lamp as recited in claim 2, wherein the oil illuminated lens surface is provided with a bead surface for ensuring uniformity of light distribution; the surface of the taper sleeve floodlight lens is provided with a prism which is used for ensuring the deflection angle of light.

4. The integrated aircraft refueling lamp as recited in claim 2 wherein the edge of the glass panel is provided with an annular groove, and a sealing ring is disposed in the groove.

5. The integrated aircraft refueling lamp as recited in claim 1 wherein the housing includes a bottom surface, a top a surface, and side B, C and D surfaces, the C and D surfaces being disposed opposite one another; the surface A is a space quadrangle, the surface B and the surface C are perpendicular to the bottom surface, the bottom surface is taken as a reference zero surface, the line-surface angle alpha between the left side of the surface A and the bottom surface is 18-20 degrees, and the line-surface angle beta between the right side of the surface A and the bottom surface is 8-10 degrees.

6. The integrated aircraft refueling lamp as recited in claim 5 wherein the C-side, the D-side and the bottom side each have a heat sink, and the heat sink surfaces formed by the heat sink of the C-side, the heat sink of the D-side and the heat sink of the bottom side are parallel to the a-side.

7. The integrated aircraft refueling lamp as recited in claim 5 wherein a front end cap is disposed on the face a and is positioned over the first cavity and conforms to the face a; and a rear end cover is arranged on the second cavity.

8. The integrated aircraft refueling lamp as recited in claim 1 wherein the driving assembly and the light source regulator convert an external input voltage into a PWM control signal of constant frequency and varying duty cycle through a pulse width modulation circuit, and the variation of the output current is regulated by adjusting the duty cycle of the PWM.

9. The integrated aircraft refueling lamp as recited in claim 2, wherein the light source assembly further comprises a fixing plate through which the TIR lens is mounted within the first cavity.

10. The integrated aircraft refueling lamp as recited in claim 2 wherein both the taper sleeve floodlight and the probe floodlight are provided as LED lights.

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