CN205221090U - Fuselage structure of aircraft - Google Patents
Fuselage structure of aircraft Download PDFInfo
- Publication number
- CN205221090U CN205221090U CN201520821570.7U CN201520821570U CN205221090U CN 205221090 U CN205221090 U CN 205221090U CN 201520821570 U CN201520821570 U CN 201520821570U CN 205221090 U CN205221090 U CN 205221090U
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- China
- Prior art keywords
- tail pipe
- body plate
- aircraft
- pipe mounting
- groove
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- 239000002828 fuel tank Substances 0.000 claims description 13
- 238000005452 bending Methods 0.000 claims description 10
- 230000013011 mating Effects 0.000 claims description 6
- 239000000446 fuel Substances 0.000 claims description 3
- 230000029058 respiratory gaseous exchange Effects 0.000 claims description 3
- 230000007547 defect Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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- Body Structure For Vehicles (AREA)
Abstract
The utility model discloses a fuselage structure of aircraft, include: auxiliary engine installing support, auxiliary engine installing support both sides respectively are equipped with a draw -in groove, the draw -in groove respectively with the bottom chucking cooperation of first fuselage board and second fuselage board front end, tail pipe mounting adjustment support and back tail pipe mounting adjustment support before install respectively first fuselage board and second fuselage board rear end, preceding tail pipe mounting adjustment support is connected fixedly respectively with back tail pipe mounting adjustment support through screw and first fuselage board and second fuselage board, first fuselage board and second fuselage board rear end top and bottom are equipped with hem and lower hem respectively, and lower hem is connected fixedly with quick -witted live source, it is connected fixedly with the fixed hem of visor to go up the hem, install the oil tank between preceding tail pipe mounting adjustment support and the back tail pipe mounting adjustment support. The utility model discloses improve the comprehensive function of fuselage structure effectively and effectively utilize the inside finite space of fuselage, make it reach structural function and structural rigidity double effect ability.
Description
Technical field
The utility model relates to a kind of aircraft, particularly relates to a kind of airframe structure of aircraft.
Background technology
Be CN201220270857.1 at application number, a kind of fuselage ring of depopulated helicopter is disclosed in the Chinese utility model patent of the fuselage ring of a kind of depopulated helicopter by name, comprise two side plates, alighting gear, tail pipe adapter plate, change speed gear box, several crossbeams, driving engine adapter plate and actuator adapter plate, described side plate is fixedly connected with described alighting gear, tail pipe adapter plate, change speed gear box, crossbeam, driving engine adapter plate, actuator adapter plate respectively, side plate contains some bending parts, and the symmetrical configuration of two side plates is identical.
Said structure focuses on structural rigidity and the outward appearance of fuselage, but the layout of the airborne equipment bear airframe structure and subsidiary engine is considered less, make the layout of a part of airborne equipment in fuselage be subject to larger restriction, and inadequate, the plug-in ratio of space availability ratio is higher.In addition, it adopts longitudinal bending to design for meeting afterbody appearance requirement at change speed gear box rear quarter panel, has a strong impact on the onboard spatial of whole afterbody mechanical property and reduction fuselage.
Utility model content
Because the above-mentioned defect of prior art, technical problem to be solved in the utility model is to provide a kind of airframe structure of aircraft, and its topology layout is reasonable, and space availability ratio is high and structural rigidity is stronger.
For achieving the above object, the utility model provides a kind of airframe structure of aircraft, comprise: subsidiary engine mounting bracket, described subsidiary engine mounting bracket both sides are respectively provided with a draw-in groove, described draw-in groove respectively with the bottom snap-fit of the first body plate and the second body plate front end;
The first described body plate and the second body plate rear end are separately installed with front tail pipe mounting and adjusting support and rear tail pipe mounting and adjusting support, and described front tail pipe mounting and adjusting support and rear tail pipe mounting and adjusting support are connected and fixed respectively by screw and the first body plate and the second body plate;
The first described body plate and the second top, body plate rear end and bottom are respectively equipped with upper hem and lower hem, and described lower hem and airborne power supply are connected and fixed;
The fixing flanging of described upper hem and over cap is connected and fixed;
Between described front tail pipe mounting and adjusting support and rear tail pipe mounting and adjusting support, fuel tank is installed.The general configuration of Here it is whole fuselage, this structure makes the space of whole fuselage be fully utilized, and solves the irrational defect of fuselage space layout in prior art.
Further, described mounting bracket is also provided with two mounting grooves, described mounting groove assembles with the first brace panel, the second brace panel respectively, and the first described brace panel and the second brace panel both sides are also connected and fixed with the first body plate and the second body plate respectively;
The second described brace panel is provided with draw-in groove, described draw-in groove be connected fixture block one end and be mounted with, draw-in groove on the described connection fixture block other end and the 3rd brace panel is mounted with, and the 3rd described brace panel two sides and the first body plate and the second body plate are connected and fixed.This structure has good booster action to whole fuselage, and its structural strength will be far longer than similar structures of the prior art.
Further, be respectively provided with a mating groove coordinated with lower hem bottom described fuel tank left and right sides, described mating groove and lower hem are by being connected and fixed.
Further, described tank bottoms is also provided with oil outlet, and left surface is provided with oil filling port, and described oil filling port is provided with type of respiration fuel lid.
Further, be provided with for making the smooth and easy through hole through tail pipe of tail pipe in the middle of described fuel tank;
Described fuel tank is also provided with arch groove, described arch groove is used for coordinating with tail pipe fixture block, described tail pipe fixture block and front tail pipe mounting and adjusting support are connected and fixed and are provided with fixture block cambered surface, described fixture block cambered surface and the clamping cambered surface be arranged on front tail pipe mounting and adjusting support are formed and clamp circle, jointly clamp tail pipe;
Described rear tail pipe mounting and adjusting support is provided with clamping cambered surface, and described tail pipe fixture block and rear tail pipe mounting and adjusting support are connected and fixed, and described clamping cambered surface forms clamping circle with the fixture block cambered surface of the tail pipe fixture block be mated, clamping tail pipe.This structure makes whole fuselage compacter.
Further, the first described body plate and the second body plate not symmetrical.
Further, the first described body plate and the second body plate are respectively provided with the second bending part and the 3rd bending part of a vertical bending.
The beneficial effects of the utility model are: the utility model effectively improves the comprehensive function of airframe structure and effectively utilizes the finite space of fuselage interior, make it reach structure function and the dual usefulness of structural rigidity.
Accompanying drawing explanation
Fig. 1 is the structural representation of the airframe structure detailed description of the invention of a kind of aircraft of the utility model.
Fig. 2 is the structural representation of the airframe structure detailed description of the invention of a kind of aircraft of the utility model.
Fig. 3 is the structural representation of the airframe structure detailed description of the invention of a kind of aircraft of the utility model.
Fig. 4 is the partial exploded view of part A in Fig. 3.
Fig. 5 is the partial exploded view of part B in Fig. 3.
Fig. 6 is the structural representation of the airframe structure detailed description of the invention of a kind of aircraft of the utility model.
Fig. 7 is the structural representation of the airframe structure detailed description of the invention of a kind of aircraft of the utility model.
Fig. 8 is the front sectional elevation of the airframe structure detailed description of the invention of a kind of aircraft of the utility model.
Fig. 9 is the second brace panel structural representation of the airframe structure detailed description of the invention of a kind of aircraft of the utility model.
Figure 10 is the 3rd brace panel structural representation of the airframe structure detailed description of the invention of a kind of aircraft of the utility model.
Detailed description of the invention
Below in conjunction with drawings and Examples, the utility model is described in further detail:
See Fig. 1 to Figure 10, a kind of airframe structure of aircraft, comprising: subsidiary engine mounting bracket 1, and described subsidiary engine mounting bracket 1 both sides are respectively provided with a draw-in groove 101, described draw-in groove 101 respectively with the bottom snap-fit of the first body plate 2 and the second body plate 3 front end;
Described mounting bracket 1 is also provided with two mounting grooves 10, described mounting groove 10 assembles with the first brace panel 11, second brace panel 13 respectively, and the first described brace panel 11 and the second brace panel 13 both sides are also connected and fixed respectively by screw and the first body plate 2 and the second body plate 3;
The second described brace panel 13 is provided with draw-in groove 9, described draw-in groove 9 be connected fixture block 14 one end and be mounted with, draw-in groove 9 on described connection fixture block 14 other end and the 3rd brace panel 12 is mounted with, and the 3rd described brace panel 12 two sides are connected and fixed by screw and the first body plate 2 and the second body plate 3;
The first described body plate 2 and the second body plate 3 rear end are separately installed with front tail pipe mounting and adjusting support 71 and rear tail pipe mounting and adjusting support 7, and described front tail pipe mounting and adjusting support 71 and rear tail pipe mounting and adjusting support 7 are connected and fixed respectively by screw and the first body plate 2 and the second body plate 3;
The first described body plate 2 and the second top, body plate 3 rear end and bottom are respectively equipped with upper hem 5 and lower hem 8, and described lower hem 8 is connected and fixed with airborne power supply;
See Fig. 8, described upper hem 5 is connected and fixed by the fixing flanging 61 of screw and over cap 6;
Between described front tail pipe mounting and adjusting support 71 and rear tail pipe mounting and adjusting support 7, fuel tank 4 is installed, respectively be provided with a mating groove 44 coordinated with lower hem 8 bottom described fuel tank 4 left and right sides, described mating groove 44 is connected by screw fixing with lower hem 8;
Also be provided with oil outlet 42 bottom described fuel tank 4, left surface is provided with oil filling port 41, and described oil filling port 41 is provided with type of respiration fuel lid 40;
Be provided with for making the smooth and easy through hole 45 passed of tail pipe in the middle of described fuel tank 4;
Described fuel tank 4 is also provided with arch groove 43, described arch groove 43 is for coordinating with tail pipe fixture block 70, described tail pipe fixture block 70 is provided with fixture block cambered surface 701, described fixture block cambered surface 701 is formed with the clamping cambered surface 702 be arranged on front tail pipe mounting and adjusting support 71 and clamps circle, jointly clamps tail pipe;
Described rear tail pipe mounting and adjusting support 7 is also provided with clamping cambered surface 702, described clamping cambered surface 702 forms clamping circle with the fixture block cambered surface 701 of the tail pipe fixture block 70 be mated, clamping tail pipe;
The airborne equipment different for satisfied installation and the requirement of subsidiary engine, the first described body plate 2 and the second body plate 3 can design respectively according to the connection requirement of distinct device, and that is they can not be symmetrical;
The first described body plate 2 and the second body plate 3 are respectively provided with the second bending part A2 of a vertical bending and roll over the 3rd crook A3, and the heating position of driving engine can be placed in outside fuselage by this structure, is conducive to the cooling of whole machinery.
More than describe preferred embodiment of the present utility model in detail.Should be appreciated that those of ordinary skill in the art just can make many modifications and variations according to design of the present utility model without the need to creative work.Therefore, all technical personnels in the art according to design of the present utility model on the basis of existing technology by the available technical scheme of logical analysis, reasoning, or a limited experiment, all should by the determined protection domain of claims.
Claims (10)
1. an airframe structure for aircraft, is characterized in that: comprising: subsidiary engine mounting bracket, and described subsidiary engine mounting bracket both sides are respectively provided with a draw-in groove, described draw-in groove respectively with the bottom snap-fit of the first body plate and the second body plate front end;
The first described body plate and the second body plate rear end are separately installed with front tail pipe mounting and adjusting support and rear tail pipe mounting and adjusting support, and described front tail pipe mounting and adjusting support and rear tail pipe mounting and adjusting support are connected and fixed respectively by screw and the first body plate and the second body plate;
The first described body plate and the second top, body plate rear end and bottom are respectively equipped with upper hem and lower hem, and described lower hem and airborne power supply are connected and fixed;
The fixing flanging of described upper hem and over cap is connected and fixed;
Between described front tail pipe mounting and adjusting support and rear tail pipe mounting and adjusting support, fuel tank is installed.
2. the airframe structure of a kind of aircraft as claimed in claim 1, it is characterized in that: described mounting bracket is also provided with two mounting grooves, described mounting groove assembles with the first brace panel, the second brace panel respectively, and the first described brace panel and the second brace panel both sides are also connected and fixed with the first body plate and the second body plate respectively.
3. the airframe structure of a kind of aircraft as claimed in claim 2, it is characterized in that: the second described brace panel is provided with draw-in groove, described draw-in groove be connected fixture block one end and be mounted with, draw-in groove on the described connection fixture block other end and the 3rd brace panel is mounted with, and the 3rd described brace panel two sides and the first body plate and the second body plate are connected and fixed.
4. the airframe structure of a kind of aircraft as claimed in claim 1, is characterized in that: be respectively provided with a mating groove coordinated with lower hem bottom described fuel tank left and right sides, and described mating groove and lower hem are by being connected and fixed.
5. the airframe structure of a kind of aircraft as claimed in claim 1, it is characterized in that: described tank bottoms is also provided with oil outlet, and left surface is provided with oil filling port, described oil filling port is provided with type of respiration fuel lid.
6. as claim 1,4,5 arbitrary as described in a kind of airframe structure of aircraft, it is characterized in that: is provided with for making the smooth and easy through hole passed of tail pipe in the middle of described fuel tank.
7. the airframe structure of a kind of aircraft as claimed in claim 1, it is characterized in that: described fuel tank is also provided with arch groove, described arch groove is used for coordinating with tail pipe fixture block, described tail pipe fixture block and front tail pipe mounting and adjusting support are connected and fixed and are provided with fixture block cambered surface, described fixture block cambered surface and the clamping cambered surface be arranged on front tail pipe mounting and adjusting support are formed and clamp circle, jointly clamp tail pipe.
8. the airframe structure of a kind of aircraft as claimed in claim 1, it is characterized in that: described rear tail pipe mounting and adjusting support is provided with clamping cambered surface, described tail pipe fixture block and rear tail pipe mounting and adjusting support are connected and fixed, described clamping cambered surface forms clamping circle with the fixture block cambered surface of the tail pipe fixture block be mated, clamping tail pipe.
9. the airframe structure of a kind of aircraft as claimed in claim 1, is characterized in that: the first described body plate and the second body plate not symmetrical.
10. the airframe structure of a kind of aircraft as claimed in claim 9, is characterized in that: the second bending part and the 3rd bending part that the first described body plate and the second body plate are respectively provided with a vertical bending.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520821570.7U CN205221090U (en) | 2015-10-22 | 2015-10-22 | Fuselage structure of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520821570.7U CN205221090U (en) | 2015-10-22 | 2015-10-22 | Fuselage structure of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205221090U true CN205221090U (en) | 2016-05-11 |
Family
ID=55896172
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520821570.7U Active CN205221090U (en) | 2015-10-22 | 2015-10-22 | Fuselage structure of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205221090U (en) |
-
2015
- 2015-10-22 CN CN201520821570.7U patent/CN205221090U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20200603 Address after: 201702 Room 802, No. 6, Lane 2265, Zhulu West Road, Xujing Town, Qingpu District, Shanghai Patentee after: Zhu Jiale Address before: 201799, Qingpu District, Shanghai, No. 7, 22, 14 Patentee before: SHANGHAI LONGYUN ALUMINIUM Co.,Ltd. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20240126 Address after: Floor 3, Building 4, No. 1501 Huibin Road, Xianghuaqiao Street, Qingpu District, Shanghai, 2017 Patentee after: Shanghai Cathy Industrial Co.,Ltd. Country or region after: China Address before: Room 802, No. 6, Lane 2265, Zhulu West Road, Xujing Town, Qingpu District, Shanghai, 201702 Patentee before: Zhu Jiale Country or region before: China |