CN110486666A - Aircraft assisted illuminating lamp - Google Patents
Aircraft assisted illuminating lamp Download PDFInfo
- Publication number
- CN110486666A CN110486666A CN201910629138.0A CN201910629138A CN110486666A CN 110486666 A CN110486666 A CN 110486666A CN 201910629138 A CN201910629138 A CN 201910629138A CN 110486666 A CN110486666 A CN 110486666A
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- Prior art keywords
- lamp
- heat
- aircraft
- dissipation
- source plate
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F21—LIGHTING
- F21S—NON-PORTABLE LIGHTING DEVICES; SYSTEMS THEREOF; VEHICLE LIGHTING DEVICES SPECIALLY ADAPTED FOR VEHICLE EXTERIORS
- F21S8/00—Lighting devices intended for fixed installation
- F21S8/02—Lighting devices intended for fixed installation of recess-mounted type, e.g. downlighters
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F21—LIGHTING
- F21V—FUNCTIONAL FEATURES OR DETAILS OF LIGHTING DEVICES OR SYSTEMS THEREOF; STRUCTURAL COMBINATIONS OF LIGHTING DEVICES WITH OTHER ARTICLES, NOT OTHERWISE PROVIDED FOR
- F21V19/00—Fastening of light sources or lamp holders
- F21V19/001—Fastening of light sources or lamp holders the light sources being semiconductors devices, e.g. LEDs
- F21V19/003—Fastening of light source holders, e.g. of circuit boards or substrates holding light sources
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F21—LIGHTING
- F21V—FUNCTIONAL FEATURES OR DETAILS OF LIGHTING DEVICES OR SYSTEMS THEREOF; STRUCTURAL COMBINATIONS OF LIGHTING DEVICES WITH OTHER ARTICLES, NOT OTHERWISE PROVIDED FOR
- F21V23/00—Arrangement of electric circuit elements in or on lighting devices
- F21V23/003—Arrangement of electric circuit elements in or on lighting devices the elements being electronics drivers or controllers for operating the light source, e.g. for a LED array
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F21—LIGHTING
- F21V—FUNCTIONAL FEATURES OR DETAILS OF LIGHTING DEVICES OR SYSTEMS THEREOF; STRUCTURAL COMBINATIONS OF LIGHTING DEVICES WITH OTHER ARTICLES, NOT OTHERWISE PROVIDED FOR
- F21V23/00—Arrangement of electric circuit elements in or on lighting devices
- F21V23/06—Arrangement of electric circuit elements in or on lighting devices the elements being coupling devices, e.g. connectors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F21—LIGHTING
- F21W—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES F21K, F21L, F21S and F21V, RELATING TO USES OR APPLICATIONS OF LIGHTING DEVICES OR SYSTEMS
- F21W2107/00—Use or application of lighting devices on or in particular types of vehicles
- F21W2107/30—Use or application of lighting devices on or in particular types of vehicles for aircraft
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F21—LIGHTING
- F21Y—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES F21K, F21L, F21S and F21V, RELATING TO THE FORM OR THE KIND OF THE LIGHT SOURCES OR OF THE COLOUR OF THE LIGHT EMITTED
- F21Y2115/00—Light-generating elements of semiconductor light sources
- F21Y2115/10—Light-emitting diodes [LED]
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Arrangement Of Elements, Cooling, Sealing, Or The Like Of Lighting Devices (AREA)
- Non-Portable Lighting Devices Or Systems Thereof (AREA)
Abstract
The present invention relates to lighting technical fields, provide a kind of aircraft assisted illuminating lamp, comprising: light source assembly includes lamp source plate and the display lamp group on lamp source plate；Driver is electrically connected to lamp source plate, the electric current of exportable at least two grades varying strengths, for adjusting the illumination intensity of display lamp group；Aviation socket is electrically connected to driver, and the lamp dimmer for being electrically connected to aircraft.Pass through setting driver, light source assembly and aviation socket, driver is electrically connected to the lamp dimmer of aircraft, operator can control driver output at least two grades of different electric currents by lamp dimmer, the difference of current strength can influence to show the illumination intensity of lamp group, so as to adjust the light that display lamp group shows different illumination intensities, therefore it can realize two grades or more of illumination intensity on aircraft, improve the applicable situation and usage experience of aircraft assisted illuminating lamp.
Description
Technical field
The invention belongs to lighting technical fields, are to be related to a kind of aircraft assisted illuminating lamp more specifically.
Background technique
Aircraft assisted illuminating lamp, i.e. aircraft lamp refer to that mounted in interior of aircraft and external traffic lights, main includes landing
Taxiing light, navigation lights, flash lamp, vertically and horizontally stabilization headlamp, cockpit light and main cabin headlamp etc., certainly,
It further include the rescue lamp for illumination in aircraft progress rescue work.According to the variability of aircraft working environment, people for
Aircraft assisted illuminating lamp it is specifically used more demanding, require the lamps and lanterns to be able to bear biggish power first and use, secondly
Also to the adjusting of the brightness of lamps and lanterns etc. requirement with higher.
However, aircraft assisted illuminating lamp generally only has one grade of illumination intensity at present, cannot achieve in use
The adjusting of the more gears of illumination intensity can not meet specific requirement when aircraft utilization very well, reduce aircraft assisted illuminating lamp
Usage experience.
Summary of the invention
The purpose of the present invention is to provide a kind of aircraft assisted illuminating lamps, it is intended to solve in the prior art, the photograph of aircraft
Bright lamp tool only has the technical issues of one grade of illumination intensity causes the usage experience of lamps and lanterns to reduce.
To solve the above problems, the embodiment of the invention provides a kind of aircraft assisted illuminating lamps, comprising:
Light source assembly, the display lamp group including lamp source plate and on the lamp source plate；
Driver, is electrically connected to the lamp source plate, and the electric current of exportable at least two grades varying strengths is described aobvious for adjusting
Show the illumination intensity of lamp group；
Aviation socket is electrically connected to the driver, and the lamp dimmer for being electrically connected to aircraft.
Further, the driver includes driving plate, and first terminal and Second terminal are electrically connected in the driving plate,
The first terminal is by driving input line to be electrically connected to the aviation socket, and the Second terminal is by driving output line to be electrically connected
It is connected to the lamp source plate.
Further, the display lamp group is LED light group.
Further, the aircraft assisted illuminating lamp further includes heat-dissipation lamp housing, and the lamp source plate is fixed on the heat dissipation
On the inside of lamp housing, the driver is set on the outside of the heat-dissipation lamp housing.
Further, it is coated with heat-conducting cream on lamp source plate side, the heat-conducting cream is held in the heat-dissipation lamp housing
Side, the display lamp group are located at the lamp source plate other side.
Further, the aircraft assisted illuminating lamp further includes the driving box on the outside of the heat-dissipation lamp housing, described
Driver is located in the driving box, and the aviation socket is fixed on the driving box, is convexly equipped on the outside of the heat-dissipation lamp housing
Multiple equally distributed radiating ribs are equipped with gap between the driving box and the radiating ribs.
Further, the first fixed column is convexly equipped on the outside of the heat-dissipation lamp housing, first fixed column protrudes the heat dissipation
Muscle deviates from one end of the heat-dissipation lamp housing, and first fixed column is held in the driving away from one end of the heat-dissipation lamp housing
Box, the driving box are convexly equipped with fixation hole corresponding with first fixed column along outside, first fixed column with it is described solid
Determine hole to be fastenedly connected by fastener.
Further, be convexly equipped with the second fixed column on the outside of the heat-dissipation lamp housing, second fixed column be equipped with it is described
The through slot communicated on the inside of heat-dissipation lamp housing, the driving output line are arranged in the through slot, and the is arranged on the driving output line
One sealing ring, first sealing ring both ends are held in described driving box one end and the second fixed column end respectively.
Further, the aircraft assisted illuminating lamp further includes protective cover, and the protective cover includes capsul and is set to
Lens on the capsul, the capsul are fixed on the inside of the heat-dissipation lamp housing, lamp source plate described in the lens face, institute
It states capsul marginal trough and is equipped with seal groove, be embedded with the second sealing ring on the seal groove, second sealing ring is held in
The groove side wall and will be on the inside of the heat-dissipation lamp housing between.
Further, the lamp source plate uses aluminum or aluminum alloy material.
The beneficial effect of aircraft assisted illuminating lamp provided by the invention is: compared with prior art, the present invention passes through
It is also electric that driver, light source assembly and aviation socket, the electric current of the exportable at least two grades varying strengths of driver, driver are set
It is connected to the lamp dimmer of aircraft, operator can be controlled driver by lamp dimmer and export different electric currents, output
Current strength difference can influence show lamp group illumination intensities, so as to adjust display lamp group show different illuminations
The light of intensity, therefore can realize two grades or more of illumination intensity on aircraft, improve being applicable in for aircraft assisted illuminating lamp
Occasion and usage experience.
Detailed description of the invention
It to describe the technical solutions in the embodiments of the present invention more clearly, below will be to embodiment or description of the prior art
Needed in attached drawing be briefly described, it should be apparent that, the accompanying drawings in the following description is only of the invention some
Embodiment for those of ordinary skill in the art without any creative labor, can also be according to these
Attached drawing obtains other attached drawings.
Fig. 1 is the schematic perspective view of aircraft assisted illuminating lamp provided in an embodiment of the present invention；
Fig. 2 is the three-dimensional structure diagram of the aviation plug of aircraft assisted illuminating lamp provided in an embodiment of the present invention；
Fig. 3 is the sectional perspective structural schematic diagram one of aircraft assisted illuminating lamp provided in an embodiment of the present invention；
Fig. 4 is the sectional perspective structural schematic diagram two of aircraft assisted illuminating lamp provided in an embodiment of the present invention；
Fig. 5 is the explosive view of Fig. 4；
Fig. 6 is the three-dimensional structure diagram of the heat-dissipation lamp housing of aircraft assisted illuminating lamp provided in an embodiment of the present invention；
Fig. 7 is the cross-sectional view of Fig. 4.
Wherein, each appended drawing reference in figure:
100- aircraft assisted illuminating lamp；1- light source assembly；2- driver；3- aviation socket；4- aviation plug；5- heat dissipation
Lamp housing；6- drives box；7- protective cover；8- fastener；9- washer；11- lamp source plate；12- shows lamp group；21- first terminal；22-
Second terminal；23- drives input line；24- drives output line；41- cable；51- radiating ribs；The gap 52-；53- first is fixed
Column；The second fixed column of 54-；The first sealing ring of 55-；56- fixed part；61- fixation hole；62- bottom case；63- upper cover；71- capsul；
72- lens；73- seal groove；The second sealing ring of 74-；The first radiating ribs of 511-；The second radiating ribs of 512-；541- through slot；542- is recessed
Slot；The first connecting hole of 621-；The second connecting hole of 631-；632- mounting groove.
Specific embodiment
The embodiment of the present invention is described below in detail, examples of the embodiments are shown in the accompanying drawings, wherein from beginning to end
Same or similar label indicates same or similar element or element with the same or similar functions.Below with reference to attached
The embodiment of figure description is exemplary, it is intended to is used to explain the present invention, and is not considered as limiting the invention.
In the description of the present invention, it is to be understood that, term " length ", " width ", "upper", "lower", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as to limit of the invention
System.
In addition, term " first ", " second " are used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance
Or implicitly indicate the quantity of indicated technical characteristic.Define " first " as a result, the feature of " second " can be expressed or
Implicitly include one or more of the features.In the description of the present invention, the meaning of " plurality " is two or more,
Unless otherwise specifically defined.
In the present invention unless specifically defined or limited otherwise, term " installation ", " connected ", " connection ", " fixation " etc.
Term shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integral；It can be mechanical connect
It connects, is also possible to be electrically connected；It can be directly connected, can also can be in two elements indirectly connected through an intermediary
The interaction relationship of the connection in portion or two elements.It for the ordinary skill in the art, can be according to specific feelings
Condition understands the concrete meaning of above-mentioned term in the present invention.
Also referring to Fig. 1 to Fig. 7, aircraft assisted illuminating lamp 100 provided in an embodiment of the present invention includes light source assembly
1, driver 2 and aviation socket 3 are applied to lighting technical field, and the illuminator for solving aircraft in the prior art only has one
The technical issues of shelves illumination intensity causes the usage experience of lamps and lanterns to reduce.
Specifically, light source assembly 1 includes lamp source plate 11 and display lamp group 12, and display lamp group 12 is set on lamp source plate 11, shows
Show lamp group 12 for emitting beam to realize the illumination functions of the lamps and lanterns；Driver 2 is electrically connected to lamp source plate 11, it is exportable at least
The electric current of two grades of varying strengths, the electric current of the varying strength exported enable to the illumination intensity of display lamp group 12 different, then
Driver 2 can be used for adjusting at least two grades of illumination intensity of display lamp group 12, to adapt to the use under aircraft varying environment；Boat
Dummy receptacle 3 is electrically connected to driver 2, and the lamp dimmer (not shown) of aircraft, i.e. aircraft are electrically connected to by aviation plug 4
Lamp dimmer be connected to the cable 41 on aviation plug 4, and aviation socket 3 is electrically connected to aviation plug 4, so that light
Mutual conduction between controller and driver 2, operator can control driver 2 by using lamp dimmer, so as to drive
The dynamic corresponding electric current for adjusting out different stalls of device 2, to adapt to the use environment of aircraft.
In the embodiment of the present invention, it may be output to by setting driver 2, light source assembly 1 and aviation socket 3, driver 2
The electric current of few two grades of varying strengths, driver 2 are also electrically connected to the lamp dimmer of aircraft by aviation socket 3, and operator can
Driver 2 is controlled by lamp dimmer and exports different electric currents, and the difference of the current strength exported can influence to show
The illumination intensity of lamp group 12 shows the light of different illumination intensities so as to adjust display lamp group 12, therefore can realize winged
Two grades or more of illumination intensity on machine improves the portability and applicable situation of aircraft assisted illuminating lamp 100.
Specifically, the particular use of the lamps and lanterns in the present embodiment is the rescue lamp on aircraft, then it needs to have more clear
Clear light.Certainly, unique restriction is not made to the particular use of lamps and lanterns herein.
In the present embodiment, the lamp dimmer on aircraft can be set to multiple, that is, correspond to the controller of multiple gears,
Each controller is the gear of a brightness of illumination.Certainly, lamp dimmer herein may be knob shape, and user can be with
The specific electric current of driver 2 is adjusted according to rotation knob, thus the illumination intensity of more accurate display lamp group 12.It is right herein
Unique restriction is not done in the setting of lamp dimmer.
Further, also referring to Fig. 3, Fig. 5 and Fig. 7, in the present embodiment, driver 2 includes driving plate (not shown),
First terminal 21 and Second terminal 22 are electrically connected in driving plate, first terminal 21 is by driving input line 23 to be electrically connected to aviation
Socket 3, Second terminal 22 are divided that is, between lamp source plate 11 and aviation socket 3 by driving output line 24 to be electrically connected to lamp source plate 11
Output line 24 and driving input line 23 Tong Guo not be driven to realize and be electrically connected, so that phase mutual conductance between driver 2 and lamp source plate 11
It is logical.In addition, aviation socket 3 is electrically connected to aviation plug 4, aviation plug 4 is electrically connected to the light on aircraft by cable 41
Controller.
Specifically, in the present embodiment, the effect of first terminal 21 and Second terminal 22 is to realize driver 2 and aviation respectively
Electric connection between socket 3, between driver 2 and lamp dimmer, so that lamp dimmer can control driver 2, from
And driver 2 is made to adjust the illumination intensity for showing lamp group 12.
Further, referring to Fig. 4, in the present embodiment, display lamp group 12 is LED light group, conducive to the flight environment of vehicle of aircraft
Under use.Certainly, display lamp group 12 may be arranged as other kinds of lamp, not make unique restriction here.
Specifically, referring to Figure 4 together and Fig. 7, display lamp group 12 includes multiple display lamps, and multiple display lamps are uniformly distributed
In on lamp source plate 11.
In the present embodiment, lamp source plate 11 uses aluminum or aluminum alloy material.The substrate of aluminum or aluminum alloy material has excellent
Thermal conductivity, it is thermally conductive very fast, preferably heat can be conducted by heat-conducting cream to heat-dissipation lamp housing 5.
Further, referring to Figure 4 together and Fig. 7, in the present embodiment, aircraft assisted illuminating lamp 100 further includes heat dissipation
Lamp housing 5, lamp source plate 11 are fixed on 5 inside of heat-dissipation lamp housing, and driver 2 is set to 5 outside of heat-dissipation lamp housing, i.e., heat-dissipation lamp housing 5 is located at lamp
Between source plate 11 and driver 2, heat spreading function is mainly played.
Specifically, in the present embodiment, display lamp group 12 is set on lamp source plate 11 and is electrically connected to the lamp source plate 11, lamp source plate
11 are set to the inside of heat-dissipation lamp housing 5 and are held in 5 inside of heat-dissipation lamp housing, and display lamp group 12 faces away from the side of heat-dissipation lamp housing 5
Setting, certainly, the light that display lamp group 12 is issued equally face away from the side of heat-dissipation lamp housing 5.Here lamp source plate 11
In the middle part of 5 inside of heat-dissipation lamp housing, and display lamp is uniformly distributed in the middle part of lamp source plate 11, and the edge of lamp source plate 11 passes through fastening
Part 8 is fixed on heat-dissipation lamp housing 5, and lamp source plate 11 is held in the inner sidewall of heat-dissipation lamp housing 5.Wherein, fastener 8 here is spiral shell
Nail, and for the fixed form of substrate, it can also select others that can not do unique limit here in a manner of fixed light source plate 11
It is fixed.
Specifically, referring to Figure 4 together to Fig. 7, in the present embodiment, heat-dissipation lamp housing 5 is convexly equipped with multiple fixed parts along edge
56, through-hole (not shown) is offered on the fixed part 56, for realizing the fixation of heat-dissipation lamp housing 5.
Further, heat-conducting cream (not shown) is coated on 11 side of lamp source plate, it is another that display lamp group 12 is located at lamp source plate 11
Side, heat-conducting cream are held in 5 inside of heat-dissipation lamp housing, so that the heat-conducting cream on lamp source plate 11 comes into full contact with 5 inside of heat-dissipation lamp housing, make
The heat obtained on lamp source plate 11 can preferably be conducted to heat-dissipation lamp housing 5, improve the specific heat load of lamp source plate 11.
Specifically, heat-conducting cream is thermal interfacial material, is generally available the heat to come out to fin conductive CPU, makes
Cpu temperature is maintained at one and can be prevented CPU with the level of steady operation and damaged because of radiating bad, and be prolonged the service life,
Wherein, heat-conducting cream is used to conduct the heat on lamp source plate 11 to heat-dissipation lamp housing 5 herein.Certainly, lamp source plate 11 and thermal louver
Other Heat Conduction Materials can also be arranged between inside in shell 5, for realizing heat on lamp source plate 11 conduction and distribute.
Further, also referring to Fig. 5 to Fig. 7, in the present embodiment, aircraft assisted illuminating lamp 100 further includes being set to
The driving box 6 in 5 outside of heat-dissipation lamp housing, driver 2 are located in driving box 6, and aviation socket 3 is fixed on driving box 6, heat-dissipation lamp housing
5 outsides are convexly equipped with multiple equally distributed radiating ribs 51.It conducts to most of heat of heat-dissipation lamp housing 5 and is dissipated by radiating ribs 51
Hair, the setting of radiating ribs 51 increase the distribution area of heat and the contact area with air, to improve lamp source plate 11 and show
Show specific heat load when lamp group 12 uses, ensure that the service performance of lamps and lanterns.It drives and is equipped with gap between box 6 and radiating ribs 51
52, it avoids contacting between radiating ribs 51 and driving box 6 and driver 2, so that the use of heat influence driver 2 is avoided, into one
Step is realized driver 2 and is protected.
In the present embodiment, interval setting between multiple radiating ribs 51, and setting annular in shape, improve radiating ribs 51 and air
Contact area.Certainly, unique restriction is not done herein for the specific distribution between the first radiating ribs 511 and the second radiating ribs 512.
Specifically, referring to Figure 6 together and Fig. 7, in the present embodiment, radiating ribs 51 include the first radiating ribs 511 and second
Radiating ribs 512, the first radiating ribs 511 protrude the setting of the second radiating ribs 512, multiple first radiating ribs 511 and multiple second heat dissipations
The setting of muscle 512 increases the area of the distribution of the heat on heat-dissipation lamp housing 5, at the same also strengthen radiating ribs 51 and air with
The contact area of air improves the efficiency that heat distributes.Wherein, box 6 and the first radiating ribs 511, driving box 6 and second is driven to dissipate
Above-mentioned gap 52 is equipped between hot muscle 512, to realize the protection to driver 2.
Referring to Fig. 5, driving box 6 includes bottom case 62 and upper cover 63, wherein bottom case 62 is fixed on heat dissipation in the present embodiment
5 outside of lamp housing, upper cover 63 are convexly equipped with the second connecting hole 631 along outside, and bottom case 62 is convexly equipped with the first connecting hole along outside correspondence
621, the first connecting hole 621 and the second connecting hole 631 are connected by fastener 8, to realize consolidating between upper cover 63 and bottom case 62
Fixed connection.Wherein, the first connecting hole 621 and the second connecting hole 631 are disposed as four.
Specifically, referring to Fig. 5, in the present embodiment, the recess of upper cover 63 is equipped with mounting groove 632, and 3 part of aviation socket is embedded
In in the mounting groove 632, and it is fixed by multiple fasteners 8, reinforce the fixation of aviation socket 3.
Further, referring to Figure 6 together and Fig. 7, in the present embodiment, the first fixed column is convexly equipped on the outside of heat-dissipation lamp housing 5
53, the first fixed column 53 protrudes one end that radiating ribs 51 deviate from heat-dissipation lamp housing 5, and the first fixed column 53 is opened in the second radiating ribs
On 512 and the second radiating ribs 512 are connected to, the first fixed column 53 is held in driving box 6 away from one end of heat-dissipation lamp housing 5.Such as Fig. 5
It is shown, drive the bottom of the bottom case 62 of box 6 to be held in the end of the first fixed column 53, so that the bottom of driving box 6 is dissipated with second
It is equipped with gap 52 between hot muscle 512, driving box 6 is avoided to be contacted with the second radiating ribs 512.Meanwhile first radiating ribs 511 protrude from
The setting of first radiating ribs 511 drives and gap 52 is equally arranged between the side and the first radiating ribs 511 of box 6, while avoiding driving
Box 6 is contacted with the first radiating ribs 511, to realize the protective effect of driving box 6.
Specifically, in the present embodiment, box 6 is driven to be convexly equipped with fixation hole 61 corresponding with the first fixed column 53 along outside, the
One fixed column 53 is fastenedly connected with fixation hole 61 by fastener 8, to realize the fixation between driving box 6 and heat-dissipation lamp housing 5.
Specifically, fastener 8 herein is set as screw, certainly, does not do unique restriction herein.
Specifically, the first fixed column 53 and fixation hole 61 are disposed as four, so that driving box 6 is only fixed with four first
The end of column 53 contacts, and increases the gap 52 between driving box 6 and the first radiating ribs 511 and the second radiating ribs 512, to avoid
Heat in first radiating ribs 511 and the second radiating ribs 512 influences the use of the driver 2 in driving box 6.Certainly, right herein
Unique restriction is not done in the quantity of the first fixed column 53.
Further, also referring to Fig. 5 to Fig. 7, in the present embodiment, the second fixed column is convexly equipped on the outside of heat-dissipation lamp housing 5
54, the second fixed column 54 is set in the second radiating ribs 512 and is connected to the second radiating ribs 512, and the second fixed column 54 and first is solid
Setting is spaced between fixed column 53.Second fixed column 54 is equipped with through slot 541, and through slot 541 is connected to 5 inside of heat-dissipation lamp housing and is connected to
Lamp source plate 11, driving output line 24 are arranged in through slot 541.As shown in figure 5, driving output line 24 passes through driving by driver 2
62 bottom of bottom case of box 6 simultaneously passes through through slot 541, drives and is arranged with the first sealing ring 55 on output line 24, first sealing ring 55
Shape cooperation driving output line 24 be arranged, be cricoid sealing ring, the first sealing ring 55 be held in driving 6 one end of box and second
Between 54 end of fixed column, i.e. the upper and lower ends of the first sealing ring 55 are held in bottom and the second fixed column of driving box 6 respectively
54 deviate from the end of heat-dissipation lamp housing 5, so that driving output line 24 is located at the inside of the first sealing ring 55 to completely cut off the external world, to keep away
Free drive moves output line 24 and contacts the first radiating ribs 511 or the second radiating ribs 512 and influence to use, to realize to driving output line 24
Protective effect.
Specifically, in the present embodiment, 54 marginal trough of the second fixed column setting fluted 542, the groove 542 is cyclic annular knot
Structure, the first sealing ring 55 are embedded in groove 542, so that the inner sidewall of the first sealing ring 55 securely fits in driving output line
24 surrounding avoids making the first radiating ribs 511 and second there are also gap between the first sealing ring 55 and driving output line 24
Heat in radiating ribs 512 is conducted to driving output line 24.The setting of groove 542 is so that the first sealing ring 55 and driving simultaneously
More firm fastening is contacted between output line 24, avoids the loosening of the two.
Further, also referring to Fig. 5 and Fig. 7, in the present embodiment, aircraft assisted illuminating lamp 100 further includes protection
Cover 7, protective cover 7 covers on light source assembly 1, and protective cover 7 is located at the inside of heat-dissipation lamp housing 5, for protecting light source assembly 1.It protects
Shield 7 includes that capsul 71 and the lens 72 on capsul 71, capsul 71 are sheathed on the edge of lens 72.Lens 72 are just
It is made to light source assembly 1, and using transparent material, the light in the display lamp group 12 of light source assembly 1 is smoothly penetrated
Lens 72 are to irradiate outside, to realize illuminating effect.Naturally, capsul 71 is located at the outer edge of lamp source plate 11, and does not contact
In lamp source plate 11.Capsul 71 is fixed on 5 inside of heat-dissipation lamp housing, and one end of specially capsul 71 is held in heat-dissipation lamp housing 5
Side, and it is fixed by fastener 8 between capsul 71 and heat-dissipation lamp housing 5, it is also sheathed on fastener 8 and is held in capsul 71
Washer 9 reinforces the fixation of fastener 8 and capsul 71, heat-dissipation lamp housing 5.
Specifically, also referring to Fig. 5 and Fig. 7, in the present embodiment, 71 marginal trough of capsul has seal groove 73, this is close
Sealing groove 73 is cricoid seal groove 73, is embedded with the second sealing ring 74 on seal groove 73, wherein the second equally setting of sealing ring 74
For cricoid sealing ring, and correspondence is embedded on seal groove 73, and the second sealing ring 74 is held in 73 side wall of seal groove and thermal louver
Between 5 inside of shell, so that the connection between 5 inside of heat-dissipation lamp housing and 71 end of capsul is even closer reliable, thus guard bit
In the substrate and display lamp group 12 of 71 inner ring of capsul.
Specifically, in the present embodiment, the installation steps of aircraft assisted illuminating lamp 100 include: first by light source assembly 1 with
Aviation socket 3 is completed to be electrically connected by conducting wire (not shown), specifically there is welding and the clamping process of conducting wire, conducting wire packet herein
Include driving output line 24 and driving input line 23；First sealing ring 55 is installed in groove 542, will be driven by fastener 8
The bottom case 62 and heat-dissipation lamp housing 5 of box 6 are fastenedly connected；Light source assembly 1 is fixed on 5 inside of heat-dissipation lamp housing, by protective cover 7 and second
Sealing ring 74 is installed on the inside of heat-dissipation lamp housing 5；Driver 2 is installed in driving box 6 and is electrically connected in light source assembly 1
And aviation socket 3；Driving 6 upper cover 63 of box is installed on bottom case 62 and aviation socket 3 is fixed on by upper cover 63 by fastener 8
On.Certainly, the sequence of installation steps herein does not do unique restriction, can mainly show final structure.
Further, in this embodiment radiating ribs 51 use aluminum or aluminum alloy material, the heat dissipation effect of heat-dissipation lamp housing 5 is improved
Fruit.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Made any modifications, equivalent replacements, and improvements etc., should all be included in the protection scope of the present invention within mind and principle.
Claims (10)
1. a kind of aircraft assisted illuminating lamp characterized by comprising
Light source assembly, the display lamp group including lamp source plate and on the lamp source plate；
Driver is electrically connected to the lamp source plate, the electric current of exportable at least two grades varying strengths, for adjusting the display lamp
The illumination intensity of group；
Aviation socket is electrically connected to the driver, and the lamp dimmer for being electrically connected to aircraft.
2. aircraft assisted illuminating lamp as described in claim 1, which is characterized in that the driver includes driving plate, described
First terminal and Second terminal are electrically connected in driving plate, the first terminal is by driving input line to be electrically connected to the aviation
Socket, the Second terminal is by driving output line to be electrically connected to the lamp source plate.
3. aircraft assisted illuminating lamp as described in claim 1, which is characterized in that the display lamp group is LED light group.
4. aircraft assisted illuminating lamp as claimed in claim 2, which is characterized in that the aircraft assisted illuminating lamp further includes
Heat-dissipation lamp housing, the lamp source plate are fixed on the inside of the heat-dissipation lamp housing, and the driver is set on the outside of the heat-dissipation lamp housing.
5. aircraft assisted illuminating lamp as claimed in claim 4, which is characterized in that be coated on lamp source plate side thermally conductive
Cream, the heat-conducting cream are held on the inside of the heat-dissipation lamp housing, and the display lamp group is located at the lamp source plate other side.
6. aircraft assisted illuminating lamp as claimed in claim 4, which is characterized in that the aircraft assisted illuminating lamp further includes
Driving box on the outside of the heat-dissipation lamp housing, the driver are located in the driving box, and the aviation socket is fixed on institute
It states on driving box, multiple equally distributed radiating ribs, the driving box and the radiating ribs is convexly equipped on the outside of the heat-dissipation lamp housing
Between be equipped with gap.
7. aircraft assisted illuminating lamp as claimed in claim 6, which is characterized in that be convexly equipped with first on the outside of the heat-dissipation lamp housing
Fixed column, first fixed column protrude one end that the radiating ribs deviate from the heat-dissipation lamp housing, and first fixed column deviates from
One end of the heat-dissipation lamp housing is held in the driving box, and the driving box is convexly equipped with corresponding with first fixed column along outside
Fixation hole, first fixed column is fastenedly connected with the fixation hole by fastener.
8. aircraft assisted illuminating lamp as claimed in claim 4, which is characterized in that be convexly equipped with second on the outside of the heat-dissipation lamp housing
Fixed column, second fixed column are equipped with the through slot communicated on the inside of the heat-dissipation lamp housing, and the driving output line is arranged in
The through slot is arranged with the first sealing ring on the driving output line, and first sealing ring both ends are held in the drive respectively
Dynamic box one end and the second fixed column end.
9. aircraft assisted illuminating lamp as claimed in claim 4, which is characterized in that the aircraft assisted illuminating lamp further includes
Protective cover, the protective cover include capsul and the lens on the capsul, and the capsul is fixed on the heat dissipation
On the inside of lamp housing, lamp source plate described in the lens face, the capsul marginal trough is equipped with seal groove, is embedded on the seal groove
There is the second sealing ring, second sealing ring is held in the groove side wall and will be between the heat-dissipation lamp housing inside.
10. aircraft assisted illuminating lamp as described in claim 1, which is characterized in that the lamp source plate uses aluminum or aluminum alloy
Material.
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| CN201910629138.0A CN110486666B (en) | 2019-07-12 | 2019-07-12 | Auxiliary lighting lamp for airplane |
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| CN201910629138.0A CN110486666B (en) | 2019-07-12 | 2019-07-12 | Auxiliary lighting lamp for airplane |
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| CN110486666B CN110486666B (en) | 2022-06-24 |
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Cited By (3)
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| CN111578244A (en) * | 2020-05-28 | 2020-08-25 | 深圳市海洋王照明工程有限公司 | Heat dissipation shell and lamp |
| CN112303521A (en) * | 2020-06-22 | 2021-02-02 | 深圳市海洋王照明工程有限公司 | Lighting lamp |
| CN112325185A (en) * | 2020-08-06 | 2021-02-05 | 海洋王照明科技股份有限公司 | Lighting device |
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