CN204014357U - Aircraft and aircraft central plate - Google Patents
Aircraft and aircraft central plate Download PDFInfo
- Publication number
- CN204014357U CN204014357U CN201420389574.8U CN201420389574U CN204014357U CN 204014357 U CN204014357 U CN 204014357U CN 201420389574 U CN201420389574 U CN 201420389574U CN 204014357 U CN204014357 U CN 204014357U
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- plate
- central plate
- framework
- hole
- aircraft
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Abstract
A kind of aircraft central plate, comprise on one central plate and central plate once, on this, central plate comprises a cover plate and a framework with central opening, this framework is connected by least three joint pins with this lower central plate, and this cover plate is removably connected in the central opening position of this framework and seals at least partly this central opening.The upper central plate of this aircraft central plate comprises cover plate and framework, and cover plate and framework removably connect, and makes in the time need to adjusting the cable of aircraft, only cover plate need be pulled down, more for convenience.The utility model also relates to a kind of aircraft with above-mentioned aircraft central plate.
Description
Technical field
The aircraft that the utility model relates to a kind of aircraft central plate and has this aircraft central plate.
Background technology
The upper and lower central plate that is designed to of the central plate of existing Multi-axis aircraft is fixed together by connector.In the time need to adjusting arranging of the power line of aircraft, holding wire, whole upper central plate must be disassembled, comparatively inconvenience.In addition, the intensity of the vertical direction of the central plate of existing aircraft and the intensity of horizontal direction and torsional direction is all not enough to some extent, causes being subject in useful life of aircraft larger restriction.
Utility model content
In view of more than, be necessary to provide a kind of cable of being convenient to adjust aircraft to arrange and can guarantee and the aircraft central plate of structural strength be also necessary to provide a kind of aircraft with this aircraft central plate.
A kind of aircraft central plate, comprise on one central plate and central plate once, on this, central plate comprises a cover plate and a framework with central opening, this framework is connected by least three joint pins with this lower central plate, and this cover plate is removably connected in the central opening position of this framework and seals at least partly this central opening.
Preferably, this cover plate fixes by least three the first fixtures and this framework.
Preferably, corresponding each joint pin of this framework is provided with a through hole, corresponding each joint pin of this cover plate is provided with a through hole, one end that each joint pin is connected with this framework is provided with one first fixing hole, the quantity of described the first fixture is identical with the quantity of described joint pin, and described the first fixture passes respectively the through hole of this cover plate and the through hole of this framework and is fixed in described the first fixing hole.
Preferably, this framework comprises the matrix of an annular, the inward flange of this matrix extends at least three connecting plates, this cover plate comprises a main body and extended at least three fixed heads in edge of this main body certainly, the quantity of described connecting plate and described fixed head is all identical with the quantity of described joint pin, the through hole of this cover plate is located at respectively described fixed head, and the through hole of this framework is located at respectively described connecting plate, and described joint pin is connected to described connecting plate.
Preferably, the outward flange of this matrix extends at least three location-plates, this lower central plate comprises a body and extended at least three mounting panels in edge of this body certainly, described location-plate is identical with the quantity of described mounting panel, the described location-plate described mounting panel that aligns respectively, is connected by two mount pads between each location-plate and the mounting panel that aligns with this location-plate.
Preferably, described location-plate is identical with the quantity of described connecting plate, the described location-plate described connecting plate that aligns respectively, and the joint pin that two mount pads that each location-plate connects and the connecting plate aliging with this location-plate are connected lays respectively at leg-of-mutton three summits.
Preferably, each mount pad is provided with a location hole towards one end of this framework, each mount pad is provided with an installing hole towards one end of this lower central plate, each location-plate is provided with two perforation, each mounting panel is provided with two perforation, each mount pad is connected with this framework by one first securing member, each mount pad is connected with this lower central plate by one second securing member, described the first securing member is fixed on described location hole through after the perforation of described location-plate, and described the second securing member is fixed on described installing hole through after the perforation of described mounting panel.
Preferably, described the first securing member and described the second securing member are screw.
Preferably, each joint pin comprises that a cylinder, is arranged at this cylinder first contiguous block and of central plate one end on this and is arranged at this first contiguous block boss of a side of this cylinder dorsad, described the first fixing hole is located at described boss and is extended to described cylinder, and described boss penetrates respectively the through hole of this framework.
Preferably, each joint pin also comprises that one is arranged at second contiguous block towards this lower central plate one end of cylinder, a this second contiguous block dorsad side of this cylinder is provided with second fixing hole that extends to this cylinder, corresponding each joint pin of this lower central plate is provided with a through hole, each joint pin is connected with this lower central plate by one second fixture, and described the second fixture is fixed on described the second fixing hole through after the through hole of this lower central plate.
Preferably, described the first fixture and described the second fixture are screw.
A kind of aircraft, comprise an aircraft central plate, this aircraft central plate comprises on one central plate and central plate once, on this, central plate comprises a cover plate and a framework with central opening, this framework is connected by least three joint pins with this lower central plate, and this cover plate is removably connected in the central opening position of this framework and seals at least partly this central opening.
Preferably, this cover plate fixes by least three the first fixtures and this framework.
Preferably, corresponding each joint pin of this framework is provided with a through hole, corresponding each joint pin of this cover plate is provided with a through hole, one end that each joint pin is connected with this framework is provided with one first fixing hole, the quantity of described the first fixture is identical with the quantity of described joint pin, and described the first fixture passes respectively the through hole of this cover plate and the through hole of this framework and is fixed in described the first fixing hole.
Preferably, this framework comprises the matrix of an annular, the inward flange of this matrix extends at least three connecting plates, this cover plate comprises a main body and extended at least three fixed heads in edge of this main body certainly, the quantity of described connecting plate and described fixed head is all identical with the quantity of described joint pin, the through hole of this cover plate is located at respectively described fixed head, and the through hole of this framework is located at respectively described connecting plate, and described joint pin is connected to described connecting plate.
Preferably, the outward flange of this matrix extends at least three location-plates, this lower central plate comprises a body and extended at least three mounting panels in edge of this body certainly, described location-plate is identical with the quantity of described mounting panel, the described location-plate described mounting panel that aligns respectively, is connected by two mount pads between each location-plate and the mounting panel that aligns with this location-plate.
Preferably, described location-plate is identical with the quantity of described connecting plate, the described location-plate described connecting plate that aligns respectively, and the joint pin that two mount pads that each location-plate connects and the connecting plate aliging with this location-plate are connected lays respectively at leg-of-mutton three summits.
Preferably, each mount pad is provided with a location hole towards one end of this framework, each mount pad is provided with an installing hole towards one end of this lower central plate, each location-plate is provided with two perforation, each mounting panel is provided with two perforation, each mount pad is connected with this framework by one first securing member, each mount pad is connected with this lower central plate by one second securing member, described the first securing member is fixed on described location hole through after the perforation of described location-plate, and described the second securing member is fixed on described installing hole through after the perforation of described mounting panel.
Preferably, described the first securing member and described the second securing member are screw.
Preferably, each joint pin comprises that a cylinder, is arranged at this cylinder first contiguous block and of central plate one end on this and is arranged at this first contiguous block boss of a side of this cylinder dorsad, described the first fixing hole is located at described boss and is extended to described cylinder, and described boss penetrates respectively the through hole of this framework.
Preferably, each joint pin also comprises that one is arranged at second contiguous block towards this lower central plate one end of cylinder, a this second contiguous block dorsad side of this cylinder is provided with second fixing hole that extends to this cylinder, corresponding each joint pin of this lower central plate is provided with a through hole, each joint pin is connected with this lower central plate by one second fixture, and described the second fixture is fixed on described the second fixing hole through after the through hole of this lower central plate.
Preferably, described the first fixture and described the second fixture are screw.
The upper central plate of this aircraft central plate comprises cover plate and framework, and cover plate and framework removably connect, and makes in the time need to adjusting the cable of aircraft, only cover plate need be pulled down, more for convenience.
Accompanying drawing explanation
Fig. 1 is the three-dimensional exploded view of the better embodiment of the utility model aircraft central plate.
Fig. 2 is the enlarged drawing of II part of the aircraft central plate of Fig. 1.
Fig. 3 is the joint pin and the first corresponding fixture and the three-dimensional assembly diagram of the second fixture of the aircraft central plate of Fig. 1.
Fig. 4 is the stereogram of mount pad of the aircraft central plate of Fig. 1.
Fig. 5 is the three-dimensional assembly diagram of the aircraft central plate of Fig. 1.
Fig. 6 is that Fig. 5 is along the cutaway view of VI-VI line.
Embodiment
Please refer to Fig. 1 and Fig. 2, be depicted as the stereochemical structure of the aircraft central plate of the utility model better embodiment, this aircraft central plate is for Multi-axis aircraft (not shown).This aircraft central plate comprises central plate 10 on, once central plate 40, a plurality of joint pin 50, a plurality of mount pad 60, a plurality of the first fixture 70, a plurality of the second fixture 80, a plurality of the first securing member 90 and a plurality of the second securing member 100.
On this, central plate 10 comprises a cover plate 20 and a framework 30.In present embodiment, described the first fixture 70, described the second fixture 80, described the first securing member 90 and described the second securing member 100 are screw.The quantity of described joint pin 50, described the first fixture 70 and described the second fixture 80 is six.The quantity of described mount pad 60, described the first securing member 90 and described the second securing member 100 is 12.Certainly, according to different demands, the quantity of described joint pin 50 and described mount pad 60 can be made suitable increase and decrease, corresponding, the quantity of described the first fixture 70, described the second fixture 80, described the first securing member 90 and described the second securing member 100 also can be done corresponding variation.
This cover plate 20 comprises a main body 22 and extended six fixed heads 24 in edge of this main body 22 certainly.In the present embodiment, six described fixed heads 24 are arranged equally spacedly.Each fixed head 24 is provided with a through hole 242.
This framework 30 comprises the matrix 32 of an annular, extended six connecting plates 34 of the inward flange of this matrix 32 and extended six location-plates 36 of outward flange of this matrix 32 certainly certainly.Described connecting plate 34 and described matrix 32 surround a central opening 38.Described connecting plate 34 is arranged equally spacedly.In the present embodiment, six described location-plates 36 are arranged equally spacedly, and the described connecting plate 34 that aligns respectively.Every a plate 34 is provided with a through hole 342.Each location-plate 36 is provided with two perforation 362.
This lower central plate 40 comprises the body 42 of a circle and extended six mounting panels 44 in edge of this body 42 certainly.In the present embodiment, six described mounting panels 44 are arranged equally spacedly.This body 42 is provided with a through hole 422 near each mounting panel 44.Each mounting panel 44 is provided with two perforation 441.
Please refer to Fig. 3, described in each, joint pin 50 comprises a cylinder 52, is arranged at one first contiguous block 54 of one end of cylinder 52, one second contiguous block 56 and that is arranged at the other end of cylinder 52 is arranged at this first contiguous block 54 boss 58 of a side of cylinder 52 dorsad.A this boss 58 dorsad side of the first contiguous block 54 is provided with a first fixing hole 582(who extends to this cylinder 52 and please refer to Fig. 2).A this second contiguous block 56 dorsad side of this cylinder 52 is provided with second fixing hole 562 that extends to cylinder 52.The shape and size of described boss 58 match with the shape and size of described through hole 342 respectively.
Please refer to Fig. 4, the top of each mount pad 60 is provided with a location hole 62.The bottom of each mount pad 60 is provided with an installing hole 64.
Please refer to Fig. 5 and Fig. 6, during assembling, the second contiguous block 56 of described joint pin 50 is positioned over to this lower central plate 40, and align the respectively through hole 422 of this lower central plate 40 of the second fixing hole 562 of described joint pin 50.Described the second fixture 80 is fixed on to described the second fixing hole 562 through after described through hole 422, makes described joint pin 50 be fixed on this lower central plate 40.The boss of described joint pin 50 58 is penetrated to the through hole 342 of this framework 30.This cover plate 20 is positioned over to this framework 30.Connecting plate 34 described in described fixed head 24 difference butts.Described the first fixture 70 is penetrated to described through hole 342 and is fixed on described the first fixing hole 582 through after described through hole 242, make this cover plate 20 removably be connected in central opening 38 positions partially enclosed this central opening 38 of this framework 30.Align the respectively mounting panel 44 of described lower central plate 40 of the location-plate 36 of described framework 30.Described mount pad 60 is positioned over to this lower central plate 40, wherein on each mounting panel 44, places two mount pads 60, each location-plate 36 is supported in the end face of two mount pads 60.By described the first securing member 90 through the location hole 62 that is fixed on described mount pad 60 after described perforation 362.By described the second securing member 100 through the installing hole 64 that is fixed on described mount pad 60 after described perforation 441.So far, this central plate has been assembled.Two mount pads 60 on each mounting panel 44 lay respectively at leg-of-mutton three summits with the joint pin 50 near this mounting panel 44.
In the time need to arranging the power line of this aircraft and data wire, only need the first firmware 70 described in pine oil, cover plate 20 is pulled down, without pulling down whole upper central plate 10.Because two mount pads 60 on each mounting panel 44 are arranged in triangle with the joint pin 50 near this mounting panel 44, this aircraft is got a promotion in rigidity, the intensity of rigidity, intensity and the torsional direction of vertical lift direction, system responses performance and the life-span of this aircraft are all improved.
In other embodiments, the quantity of fixed head 24, connecting plate 34, location-plate 36, mounting panel 44 and joint pin 50 is not limited to six, can be also three, four, eight or other quantity.
In other embodiments, the first fixture 70 can not be connected with joint pin 50 yet, the first fixture 70 can be only for fixing cover plate 20 and framework 30, and like this, joint pin 50 can be connected by welding, riveted joint and alternate manner with framework 30 and lower central plate 40.
In other embodiments, between cover plate 20 and framework 30, can interfix by a plurality of pins, or a plurality of draw-in grooves are set on framework 30, a plurality of grabs that are placed in described draw-in groove are set on cover plate 20, can make cover plate 20 removably be connected in central opening 38 positions of this framework 30.
Claims (12)
1. an aircraft central plate, comprise on one central plate and central plate once, it is characterized in that: on this, central plate comprises a cover plate and a framework with central opening, this framework is connected by least three joint pins with this lower central plate, and this cover plate is removably connected in the central opening position of this framework and seals at least partly this central opening.
2. aircraft central plate as claimed in claim 1, is characterized in that: this cover plate fixes by least three the first fixtures and this framework.
3. aircraft central plate as claimed in claim 2, it is characterized in that: corresponding each joint pin of this framework is provided with a through hole, corresponding each joint pin of this cover plate is provided with a through hole, one end that each joint pin is connected with this framework is provided with one first fixing hole, the quantity of described the first fixture is identical with the quantity of described joint pin, and described the first fixture passes respectively the through hole of this cover plate and the through hole of this framework and is fixed in described the first fixing hole.
4. aircraft central plate as claimed in claim 3, it is characterized in that: this framework comprises the matrix of an annular, the inward flange of this matrix extends at least three connecting plates, this cover plate comprises a main body and extended at least three fixed heads in edge of this main body certainly, the quantity of described connecting plate and described fixed head is all identical with the quantity of described joint pin, the through hole of this cover plate is located at respectively described fixed head, the through hole of this framework is located at respectively described connecting plate, and described joint pin is connected to described connecting plate.
5. aircraft central plate as claimed in claim 4, it is characterized in that: the outward flange of this matrix extends at least three location-plates, this lower central plate comprises a body and extended at least three mounting panels in edge of this body certainly, described location-plate is identical with the quantity of described mounting panel, the described location-plate described mounting panel that aligns respectively, is connected by two mount pads between each location-plate and the mounting panel that aligns with this location-plate.
6. aircraft central plate as claimed in claim 5, it is characterized in that: described location-plate is identical with the quantity of described connecting plate, the described location-plate described connecting plate that aligns respectively, the joint pin that two mount pads that each location-plate connects and the connecting plate aliging with this location-plate are connected lays respectively at leg-of-mutton three summits.
7. aircraft central plate as claimed in claim 5, it is characterized in that: each mount pad is provided with a location hole towards one end of this framework, each mount pad is provided with an installing hole towards one end of this lower central plate, each location-plate is provided with two perforation, each mounting panel is provided with two perforation, each mount pad is connected with this framework by one first securing member, each mount pad is connected with this lower central plate by one second securing member, described the first securing member is fixed on described location hole through after the perforation of described location-plate, described the second securing member is fixed on described installing hole through after the perforation of described mounting panel.
8. aircraft central plate as claimed in claim 7, is characterized in that: described the first securing member and described the second securing member are screw.
9. aircraft central plate as claimed in claim 4, it is characterized in that: each joint pin comprises that a cylinder, is arranged at this cylinder first contiguous block and of central plate one end on this and is arranged at this first contiguous block boss of a side of this cylinder dorsad, described the first fixing hole is located at described boss and is extended to described cylinder, and described boss penetrates respectively the through hole of this framework.
10. aircraft central plate as claimed in claim 9, it is characterized in that: each joint pin also comprises that one is arranged at second contiguous block towards this lower central plate one end of cylinder, a this second contiguous block dorsad side of this cylinder is provided with second fixing hole that extends to this cylinder, corresponding each joint pin of this lower central plate is provided with a through hole, each joint pin is connected with this lower central plate by one second fixture, and described the second fixture is fixed on described the second fixing hole through after the through hole of this lower central plate.
11. aircraft central plates as claimed in claim 10, is characterized in that: described the first fixture and described the second fixture are screw.
12. 1 kinds of aircraft, comprise just like the aircraft central plate described in claim 1-11 any one.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420389574.8U CN204014357U (en) | 2014-07-15 | 2014-07-15 | Aircraft and aircraft central plate |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420389574.8U CN204014357U (en) | 2014-07-15 | 2014-07-15 | Aircraft and aircraft central plate |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204014357U true CN204014357U (en) | 2014-12-10 |
Family
ID=52054289
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420389574.8U Expired - Fee Related CN204014357U (en) | 2014-07-15 | 2014-07-15 | Aircraft and aircraft central plate |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204014357U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106275369A (en) * | 2015-05-21 | 2017-01-04 | 中国科学院遥感与数字地球研究所 | Unmanned plane mounting disc |
-
2014
- 2014-07-15 CN CN201420389574.8U patent/CN204014357U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106275369A (en) * | 2015-05-21 | 2017-01-04 | 中国科学院遥感与数字地球研究所 | Unmanned plane mounting disc |
| CN106275369B (en) * | 2015-05-21 | 2018-04-10 | 中国科学院遥感与数字地球研究所 | Unmanned plane mounting disc |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141210 |