CN104613397B - A kind of undercarriage is put into an indicator light - Google Patents
A kind of undercarriage is put into an indicator light Download PDFInfo
- Publication number
- CN104613397B CN104613397B CN201310535576.3A CN201310535576A CN104613397B CN 104613397 B CN104613397 B CN 104613397B CN 201310535576 A CN201310535576 A CN 201310535576A CN 104613397 B CN104613397 B CN 104613397B
- Authority
- CN
- China
- Prior art keywords
- lamp
- lampshade
- lamp body
- tail
- electric connector
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 239000005388 borosilicate glass Substances 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 239000000758 substrate Substances 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 229910001385 heavy metal Inorganic materials 0.000 description 2
- 238000009877 rendering Methods 0.000 description 2
- 231100000331 toxic Toxicity 0.000 description 2
- 230000002588 toxic effect Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F21—LIGHTING
- F21S—NON-PORTABLE LIGHTING DEVICES; SYSTEMS THEREOF; VEHICLE LIGHTING DEVICES SPECIALLY ADAPTED FOR VEHICLE EXTERIORS
- F21S43/00—Signalling devices specially adapted for vehicle exteriors, e.g. brake lamps, direction indicator lights or reversing lights
- F21S43/50—Signalling devices specially adapted for vehicle exteriors, e.g. brake lamps, direction indicator lights or reversing lights characterised by aesthetic components not otherwise provided for, e.g. decorative trim, partition walls or covers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F21—LIGHTING
- F21S—NON-PORTABLE LIGHTING DEVICES; SYSTEMS THEREOF; VEHICLE LIGHTING DEVICES SPECIALLY ADAPTED FOR VEHICLE EXTERIORS
- F21S43/00—Signalling devices specially adapted for vehicle exteriors, e.g. brake lamps, direction indicator lights or reversing lights
-
- 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
- F21V17/00—Fastening of component parts of lighting devices, e.g. shades, globes, refractors, reflectors, filters, screens, grids or protective cages
- F21V17/10—Fastening of component parts of lighting devices, e.g. shades, globes, refractors, reflectors, filters, screens, grids or protective cages characterised by specific fastening means or way of fastening
- F21V17/12—Fastening of component parts of lighting devices, e.g. shades, globes, refractors, reflectors, filters, screens, grids or protective cages characterised by specific fastening means or way of fastening by screwing
-
- 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
-
- 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
- F21V3/00—Globes; Bowls; Cover glasses
- F21V3/04—Globes; Bowls; Cover glasses characterised by materials, surface treatments or coatings
- F21V3/06—Globes; Bowls; Cover glasses characterised by materials, surface treatments or coatings characterised by the material
- F21V3/061—Globes; Bowls; Cover glasses characterised by materials, surface treatments or coatings characterised by the material the material being glass
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Arrangement Of Elements, Cooling, Sealing, Or The Like Of Lighting Devices (AREA)
- Non-Portable Lighting Devices Or Systems Thereof (AREA)
- Fastening Of Light Sources Or Lamp Holders (AREA)
Abstract
The invention discloses a kind of undercarriages to be put into an indicator light, including：Tail portion electric connector, lamp body, circuit board, the crown top of burner, the lampshade being connected together；The tail portion electric connector tail end has the workpiece connecting hole passed through for aircraft wire, and front end is provided with the annular groove for being connect with lamp body;The lamp body is hollow structure, and tail end is connected by annular groove with the tail portion electric connector, and front end is provided with the boss for placing circuit board, and have among the boss be used for connecting wire by connecting hole；Include the power supply module and light source assembly that are connect with supply line on the circuit board；The crown top of burner is tubular structure, is connected with lamp body；The lampshade is hollow cover body structure, and cover mouth size is more than crown top of burner upper edge size, and lampshade is stretched into from crown top of burner lower end, and is stretched out from crown top of burner upper end, and crown top of burner upper end toe-in, and lampshade lower end is interference fitted with crown top of burner upper end.The configuration of the present invention is simple, connection is reliable, long lifespan.
Description
Technical Field
The invention belongs to an aircraft external light signal indicating product, and relates to an improvement of an aircraft landing gear in-place indicating lamp.
Background
The electric conversion efficiencies of incandescent lamps, fluorescent lamps and LED lamps are respectively as follows: 3%, 15% and 20% -40%. At present, the selection of light sources by an aircraft external light signal indicator lamp is mainly comprehensively considered from the light efficiency, the service life and the reliability, and an LED light source is widely adopted.
However, the existing aircraft external light signal indicator lamp adopts an LED light source, and has the defects of backward light source model, short service life, easy damage, weak luminous intensity, small range and the like. Meanwhile, the LED light source and the structural shell are designed separately, the power line contact part of the light source base is easy to loosen, the reliability is poor, the light emitting angle is small, the heat dissipation design is not carried out, and the service life is short.
Disclosure of Invention
The purpose of the invention is as follows: the indicating lamp for putting the landing gear in place has the advantages of simple structure, high reliability and large light-emitting range.
The technical scheme adopted by the invention for solving the technical problems is as follows:
an aircraft landing gear in-position indicator light comprising: the tail electric connector, the lamp body, the circuit board, the lamp cap and the lamp shade are connected together;
the tail end of the tail electric connector is provided with a workpiece connecting hole for the aircraft lead to pass through, and the front end of the tail electric connector is provided with a ring groove for connecting with a lamp body;
the lamp body is of a hollow structure, the tail end of the lamp body is connected with the tail electric connector through a ring groove, the front end of the lamp body is provided with a boss for placing a circuit board, and a connecting hole for connecting a lead to pass through is formed in the middle of the boss;
the circuit board comprises a power supply assembly and a light source assembly which are connected with a power supply circuit;
the lamp cap is of a cylindrical structure and is matched and connected with the lamp body;
the lampshade is of a hollow lampshade body structure, the size of the lampshade opening is larger than that of the upper edge of the lamp cap, the lampshade extends into the lower end of the lamp cap and extends out of the upper end of the lamp cap, the upper end of the lamp cap is inwardly converged, and the lower end of the lampshade is in interference fit with the upper end of the lamp cap.
The circuit board is two single-sided aluminum substrates arranged back to back.
And the tail end of the lamp body is also provided with a connecting hole for connecting and fixing with a tail electric connector or an airplane structure.
The connecting holes at the tail end of the lamp body are divided into two groups with different sizes, each group is three, and the connecting holes of different groups are arranged at intervals.
The connecting holes are different in size, wherein three puller bolts or screws are arranged on the connecting holes with smaller apertures at the tail end of the lamp body and embedded in the ring grooves of the tail electric connector.
The outer surface of the lamp body is provided with an annular bulge with external threads, and the annular bulge is in threaded connection with the lower end of the lamp cap.
The lamp body is connected with the lower end of the lamp cap in a clamping manner.
The lampshade is characterized by being made of borosilicate glass materials.
The invention has the advantages and effects that:
the airplane landing gear in-place indicator lamp is simple in structure, reliable in connection and long in service life through the assembly design of the tail electric connector, the lamp body, the circuit board, the lamp cap and the lamp shade.
In addition, the device has the advantages of large light-emitting angle, high light-emitting efficiency, safe voltage power supply, no toxic heavy metal, high color rendering index, lowest power consumption under the same brightness and the like.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.
Drawings
The present invention will be described in detail below with reference to the accompanying drawings so that the above advantages of the present invention will be more apparent. Wherein,
FIG. 1 is a schematic view of the aircraft landing gear in position indicator light of the present invention;
FIG. 2 is an exploded view of the aircraft landing gear in position indicator light of the present invention, wherein 1-tail electrical connector, 2-lamp body, 3-circuit board, 4-lamp cap, 5-lamp housing;
FIG. 3 is a rear schematic view of the rear electrical connector;
FIG. 4 is a side view of the rear electrical connector;
FIG. 5 is a front view of the tail electrical connector;
figure 6 is a circuit diagram of an aircraft landing gear in position indicator light of the present invention.
Detailed Description
The following detailed description of the embodiments of the present invention will be provided with reference to the drawings and examples, so that how to apply the technical means to solve the technical problems and achieve the technical effects can be fully understood and implemented. It should be noted that, as long as there is no conflict, the embodiments and the features of the embodiments of the present invention may be combined with each other, and the technical solutions formed are within the scope of the present invention.
Referring to fig. 1 and 2, fig. 1 is a schematic structural view of an airplane landing gear in-place indicator light of the present invention, and fig. 2 is an exploded view of the airplane landing gear in-place indicator light of the present invention. The aircraft landing gear in-place indicator lamp comprises a tail electric connector 1, a lamp body 2, a circuit board 3, a lamp cap 4 and a lamp shade 5.
Referring to fig. 3, 4 and 5, the tail end of the tail electrical connector is a workpiece connection hole for an aircraft wire to pass through. The front end of the tail electric connector is provided with a ring groove used for being connected with the lamp body.
The lamp body is of a hollow structure with an annular bulge in the middle, two groups of connecting holes with different sizes are uniformly distributed at intervals at the tail end of the lamp body, and the adjacent connecting holes are different in size. The middle bulge is provided with external threads, and the front end of the middle bulge is a boss with a connecting hole in the middle, so that the circuit board can be placed in the boss, and the light-emitting range is large. The circuit board comprises two single-sided aluminum substrates of a power supply assembly and a light source assembly, and has better heat dissipation performance. The lamp cap is of a cylindrical structure, and the inner surface of the lamp cap is provided with an internal thread matched with the annular convex external thread of the lamp body. The lampshade is of a hollow lampshade body structure, the size of the lampshade opening is slightly larger than the size of the upper edge of the lamp cap, the lampshade opening and the lamp cap are connected in an interference fit mode, and the lampshade is made of borosilicate glass materials and has high environmental adaptability.
When the airplane landing gear is put in place and the indicator lamp is assembled, the tail electric connector is connected with the lamp body through three puller bolts, and the three puller bolts are arranged on a connecting hole with a smaller tail end aperture of the lamp body and are embedded in the ring groove of the tail electric connector. The circuit board is fixed on the lamp body boss through a bolt and is communicated with a power supply circuit so as to ensure a larger light-emitting angle. The lampshade extends into the lamp cap from the lower end of the lamp cap and extends out from the upper end of the lamp cap, the lower end of the lampshade is in interference fit with the upper end of the lamp cap, and the lower end of the lampshade is in threaded connection with the annular bulge on the outer surface of the lamp body.
Please refer to fig. 6, which is a circuit diagram of the landing gear in-position indicator light circuit board according to the present invention. The circuit board comprises a rectifier bridge, two current-limiting resistors and two groups of LED light sources. Each current-limiting resistor is connected with one group of LED light sources in series and then connected with the other group of LED light sources in parallel, and then the current-limiting resistors are integrally connected with a rectifier bridge in series to form a loop, and the power supply input end of the rectifier bridge is connected with two 20# power supply wires of the airplane, namely direct current +28V and the ground wire. Because each path of light source is provided with the current-limiting resistor, the voltage distributed to the light source can not exceed the rated voltage, and the input end of the circuit is provided with the rectifier bridge, the relation of the positive electrode and the negative electrode is not needed to be considered when the wiring is installed, the device is effectively prevented from being burnt down when the positive electrode and the negative electrode are connected,
the invention relates to an indication lamp for indicating the landing gear in place, which has the main advantages that: 1. the wiring mode is simple and reliable, the improvement of the tail electric connector enables the wiring mode to be simpler and firmer, the product maintainability is good, and the whole maintenance process costs shorter time on the assembly and disassembly of the product;
2. the light source adopts a high-brightness low-power LED, which has the advantages of high luminous efficiency, long service life, good performance, safe voltage power supply, no toxic heavy metal, high color rendering index and lowest power consumption under the same brightness;
3. the luminous intensity is high, the range is wide, the design of the product reaches the luminous range of 120 degrees, the central light intensity is 20cd, and the edge light intensity can reach 10cd at the weakest.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that changes may be made in the embodiments and/or equivalents thereof without departing from the spirit and scope of the invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. An aircraft landing gear in-place indicator light, comprising: the tail electric connector, the lamp body, the circuit board, the lamp cap and the lamp shade are connected together;
the tail end of the tail electric connector is provided with a workpiece connecting hole for the aircraft lead to pass through, and the front end of the tail electric connector is provided with a ring groove for connecting with a lamp body;
the lamp body is of a hollow structure, the tail end of the lamp body is connected with the tail electric connector through a ring groove, the front end of the lamp body is provided with a boss for placing a circuit board, and a connecting hole for connecting a lead to pass through is formed in the middle of the boss;
the circuit board comprises a power supply assembly and a light source assembly which are connected with a power supply circuit;
the lamp cap is of a cylindrical structure and is matched and connected with the lamp body;
the lampshade is of a hollow lampshade body structure, the size of a lampshade opening is larger than that of an upper edge of the lamp cap, the lampshade extends into the lower end of the lamp cap and extends out of the upper end of the lamp cap, the upper end of the lamp cap is converged inwards, and the lower end of the lampshade is in interference fit with the upper end of the lamp cap;
the circuit board is two single-sided aluminum substrates arranged back to back;
and the tail end of the lamp body is provided with a connecting hole for connecting and fixing with a tail electric connector or an airplane structure.
2. An aircraft landing gear in-place indicator light according to claim 1, wherein the outer surface of the light body is provided with an annular projection with external threads and is threadedly connected to the lower end of the cap.
3. An aircraft landing gear in place indicator light as claimed in claim 1, wherein the light body is snap-fit to the lower end of the cap.
4. An aircraft landing gear in-place indicator light according to any of claims 1 to 3, wherein the light cover is made from a borosilicate glass material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310535576.3A CN104613397B (en) | 2013-11-04 | 2013-11-04 | A kind of undercarriage is put into an indicator light |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310535576.3A CN104613397B (en) | 2013-11-04 | 2013-11-04 | A kind of undercarriage is put into an indicator light |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104613397A CN104613397A (en) | 2015-05-13 |
| CN104613397B true CN104613397B (en) | 2018-07-03 |
Family
ID=53147980
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310535576.3A Active CN104613397B (en) | 2013-11-04 | 2013-11-04 | A kind of undercarriage is put into an indicator light |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104613397B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105346707B (en) * | 2015-12-02 | 2023-08-15 | 上海航空电器有限公司 | Undercarriage control switch with day-night conversion indication function |
| CN107226200B (en) * | 2016-03-25 | 2019-11-15 | 哈尔滨飞机工业集团有限责任公司 | A kind of landing gear position optical indicating device |
| CN207729319U (en) * | 2017-12-05 | 2018-08-14 | 湖南粤港模科实业有限公司 | A kind of anti-glare light with LED module light source |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3741858C2 (en) * | 1987-12-10 | 1999-05-27 | Klotz Willi | landing gear |
| GB0715887D0 (en) * | 2007-08-15 | 2007-09-26 | Airbus Uk Ltd | Aircraft light unit |
| CN203147559U (en) * | 2013-01-30 | 2013-08-21 | 上海航空电器有限公司 | Airfoil navigation lamp |
| CN203586028U (en) * | 2013-11-04 | 2014-05-07 | 西安飞豹科技发展公司 | Aircraft landing gear put-in-place indicator lamp |
-
2013
- 2013-11-04 CN CN201310535576.3A patent/CN104613397B/en active Active
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| Publication number | Publication date |
|---|---|
| CN104613397A (en) | 2015-05-13 |
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| CB02 | Change of applicant information | ||
| CB02 | Change of applicant information |
Address after: 710089 Shaanxi Province, Xi'an city Yanliang District People's Road West, No. 100 South Applicant after: Xi'an Feibao Technology Co. Ltd. Address before: 710089 Shaanxi Province, Xi'an city Yanliang District People's Road West, No. 100 South Applicant before: Xi'an Feibao Technology Development Co., Ltd. |
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