CN205675219U - A kind of fuselage and sphere frame docking structure - Google Patents
A kind of fuselage and sphere frame docking structure Download PDFInfo
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- CN205675219U CN205675219U CN201620570289.5U CN201620570289U CN205675219U CN 205675219 U CN205675219 U CN 205675219U CN 201620570289 U CN201620570289 U CN 201620570289U CN 205675219 U CN205675219 U CN 205675219U
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- interfacing part
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- 238000003032 molecular docking Methods 0.000 title claims abstract description 33
- 230000001154 acute effect Effects 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 3
- 230000005540 biological transmission Effects 0.000 abstract description 2
- 208000037656 Respiratory Sounds Diseases 0.000 abstract 1
- 238000004519 manufacturing process Methods 0.000 description 3
- 210000000744 eyelid Anatomy 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 210000003128 head Anatomy 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
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Abstract
nullThis utility model provides a kind of fuselage and sphere frame docking structure，Including Y section bar (1)、Interfacing part one (2)、Interfacing part two (3)、Interfacing part three (4) and docking band plate (5)，Y section bar (1) includes straight portion (11) and forked section (12)，Straight portion (11) is divided into straight first paragraph (111) and straight second segment (112)，Straight second segment (112) and forked section (12) angle at 45 °，Interfacing part one (2) is connected on straight second segment (112)，Interfacing part two (3) and interfacing part three (4) be all cross section be the angle section of L-shaped，Interfacing part two (3)、Straight first paragraph (111) and interfacing part three (4) stack gradually and connect into entirety with connector，The another side of interfacing part two (3) and interfacing part three (4) all passes through connector and is connected with docking band plate (5).This utility model power transmission is preferable, reduces quantity and the quantity of part of connector, reduces the probability that damage and the crackle of structure are produced by connector.
Description
Technical field
This utility model belongs to aircraft pressure bulkhead structure technology, is specifically related to fuselage and sphere frame docking structure.
Background technology
Pressure bulkhead on aircraft, lay respectively at head and rear body, be the separating surface of aircraft air-tight section and non-hermetically sealed district.
Pressure bulkhead bears the gas pressure loads of engine room inside, provides the air pressure environment of safety and comfort for passenger.It is positioned at the gas of rear body
Close frame is generally divided into flat board frame, sphere frame and combined pressure bulkhead.In Large Civil Aircraft, general employing sphere frame, so may be used
To improve the service efficiency of structure, reducing aero-structure weight, manufacturing process is ripe, low cost.
Fuselage is more complicated with docking of sphere mount structure, and fuselage is the circle of the bubble tee section of an irregular curve composition
Cylinder, and sphere frame is usually a spherical crown curved surface.During two kinds of curved-surface structure docking, the gas of air-tight section well-formed to be considered
Close property, it is also contemplated that the efficiency of aircraft cabin space utilization, and the design and the manufacture difficulty that thus result in docking structure are the biggest.This
Outward, the angle between sphere frame covering and fuselage skin is that the assembling of docking structure brings many problems.
Utility model content
The purpose of this utility model is to provide a kind of fuselage and sphere frame docking structure, improves docking structure stress feelings
Condition.
The purpose of this utility model is achieved through the following technical solutions: a kind of fuselage and sphere frame docking structure, including Y type
Material, interfacing part one, interfacing part two, interfacing part three and docking band plate, described Y section bar includes straight portion and is arranged in described straight
Forked section in part, wherein, described straight portion is divided into straight first paragraph and straight second segment, institute by described forked section
Stating straight second segment to have angle with described forked section, described interfacing part section one by one is connected on described straight second segment, institute
State interfacing part two and described interfacing part three be all cross sectional shape be the section bar of dihedral, described interfacing part two, described straight
First paragraph and described interfacing part three while stacking gradually and connecting integral with connector, the another side of described interfacing part two
All pass through connector with the another side of described interfacing part three to be connected with described docking band plate.
Preferably, described straight second segment and described forked section acute angle at 45 °.
Preferably, round-corner transition is passed through in described straight portion and described forked section junction.
Preferably, described interfacing part two and described interfacing part three be all cross sectional shape be the right angle section bar of L-shaped.
A kind of fuselage provided by the utility model has the beneficial effects that with sphere frame docking structure, and power transmission is preferable, system
Making and assemble simple, low cost of manufacture, the use of Y section bar can reasonably utilize the angle of structure to fuselage curved surface and sphere frame
Curved surface docks.
Accompanying drawing explanation
Fig. 1 is fuselage of the present utility model and sphere frame docking structure schematic diagram.
Reference:
1-Y section bar, 2-interfacing part one, 3-interfacing part two, 4-interfacing part three, 5-dock band plate, 6-sphere frame covering, 7-machine
Body eyelid covering, 8-stringer joint, 11-straight portion, 12-forked section, 111-is straight first paragraph, 112-is straight second segment.
Detailed description of the invention
Clearer, below in conjunction with this utility model for the purpose making this utility model implement, technical scheme and advantage
Accompanying drawing in embodiment, is further described in more detail the technical scheme in this utility model embodiment.In the accompanying drawings, ad initio
Represent same or similar element to same or similar label eventually or there is the element of same or like function.Described reality
Executing example is a part of embodiment of the present invention rather than whole embodiments.The embodiment described below with reference to accompanying drawing is to show
Example, it is intended to be used for explaining this utility model, and it is not intended that to restriction of the present utility model.Based in this utility model
Embodiment, the every other embodiment that those of ordinary skill in the art are obtained under not making creative work premise,
Broadly fall into the scope of this utility model protection.
Below in conjunction with the accompanying drawings this utility model fuselage is described in further details with sphere frame docking structure.
As it is shown in figure 1, fuselage and sphere frame docking structure, including Y section bar 1, interfacing part 1, interfacing part 23, interfacing part
34 include straight portion 11 and the forked section 12 being arranged in straight portion 11, wherein, bifurcated with docking band plate 5, Y section bar 1
Straight portion 11 is divided into straight first paragraph 111 and straight second segment 112, straight second segment 112 and forked section 12 by part 12
Have angle, due to an angle, thus ensure that forked section 12 can be connected with sphere frame covering 6 curved surface, straight second
Angle between section 112 and forked section 12, does not interferes with stringer joint 8, fuselage skin 7 and interfacing part 34,
Preferably angle is 45 ° of acute angles, and straight portion 11 passes through round-corner transition with forked section 12 junction, it is to avoid stress is concentrated and made
Becoming junction cracking, interfacing part one 2 one sections is connected on straight second segment 112, and another section of interfacing part 1 is bent into a C font,
Y section bar is this while be connected while the connected mode that is connected with interfacing part 1 with sphere frame covering 6, is to exist for bearing covering
Radial component under airtight load.The interfacing part 23 of the present embodiment and interfacing part 34 all preferred cross-sections are shaped as the right angle of L-shaped
Section bar, first paragraph 111 interfacing part 23, straight and interfacing part 34 while stacking gradually and connecting into one with connector
Entirety, the another side of interfacing part 23 and the another side of interfacing part 34 all pass through connector and are connected with docking band plate 5, due to docking
Part 23 and interfacing part 34 be all cross sectional shape be the right angle section bar of L-shaped, and then ensure that Y section bar and docking band plate 5 vertical
Fixing of installation, interfacing part 23 and 34 pairs of Y section bars 1 of interfacing part is more firm, away from side and the machine of Y section bar 1 in docking band plate 5
Body eyelid covering 7 connects, and the interpolation of docking band plate 5 ensure that the intensity of fuselage and sphere frame joint, stringer joint 8 are connected to docking
Near the two ends of the side of Y section bar 1 in band plate 5, to ensure fuselage load Path of Force Transfer.
The above, detailed description of the invention the most of the present utility model, but protection domain of the present utility model does not limit to
In this, any those familiar with the art in the technical scope that this utility model discloses, the change that can readily occur in
Change or replace, all should contain within protection domain of the present utility model.Therefore, protection domain of the present utility model should be with described
Scope of the claims is as the criterion.
Claims (4)
1. a fuselage and sphere frame docking structure, it is characterised in that include Y section bar (1), interfacing part one (2), interfacing part two
(3), interfacing part three (4) and docking band plate (5), described Y section bar (1) includes straight portion (11) and is arranged in described straight portion
(11) forked section (12) on, wherein, described straight portion (11) is divided into straight first paragraph by described forked section (12)
(111) and straight second segment (112), described straight second segment (112) has angle with described forked section (12), described docking
Part one (2) one section is connected on described straight second segment (112), and described interfacing part two (3) and described interfacing part three (4) are all to cut
Face is shaped as the section bar of dihedral, described interfacing part two (3), described straight first paragraph (111) and described interfacing part three (4)
While stack gradually and with connector connect integral, the another side of described interfacing part two (3) and described interfacing part three (4)
Another side all pass through connector and be connected with described docking band plate (5).
Fuselage the most according to claim 1 and sphere frame docking structure, it is characterised in that described straight second segment (112)
With described forked section (12) acute angle at 45 °.
Fuselage the most according to claim 1 and sphere frame docking structure, it is characterised in that described straight portion (11) and institute
State forked section (12) junction and pass through round-corner transition.
Fuselage the most according to claim 1 and sphere frame docking structure, it is characterised in that described interfacing part two (3) and institute
State interfacing part three (4) be all cross sectional shape be the right angle section bar of L-shaped.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620570289.5U CN205675219U (en) | 2016-06-13 | 2016-06-13 | A kind of fuselage and sphere frame docking structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620570289.5U CN205675219U (en) | 2016-06-13 | 2016-06-13 | A kind of fuselage and sphere frame docking structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205675219U true CN205675219U (en) | 2016-11-09 |
Family
ID=57432653
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620570289.5U Active CN205675219U (en) | 2016-06-13 | 2016-06-13 | A kind of fuselage and sphere frame docking structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205675219U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107463746A (en) * | 2017-08-03 | 2017-12-12 | 中国航空工业集团公司西安飞机设计研究所 | Fuselage bulkhead circumference stress computational methods under a kind of airtight load |
-
2016
- 2016-06-13 CN CN201620570289.5U patent/CN205675219U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107463746A (en) * | 2017-08-03 | 2017-12-12 | 中国航空工业集团公司西安飞机设计研究所 | Fuselage bulkhead circumference stress computational methods under a kind of airtight load |
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|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |