CN108177788A - A kind of aircraft body structure - Google Patents
A kind of aircraft body structure Download PDFInfo
- Publication number
- CN108177788A CN108177788A CN201810000635.XA CN201810000635A CN108177788A CN 108177788 A CN108177788 A CN 108177788A CN 201810000635 A CN201810000635 A CN 201810000635A CN 108177788 A CN108177788 A CN 108177788A
- Authority
- CN
- China
- Prior art keywords
- plates
- plate
- aircraft body
- body structure
- fixture block
- 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.)
- Granted
Links
- 238000009434 installation Methods 0.000 abstract description 5
- 238000003466 welding Methods 0.000 abstract description 4
- 230000003111 delayed effect Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 238000005476 soldering Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Plates (AREA)
Abstract
The present invention relates to technical field of aircraft structure design, and in particular to a kind of aircraft body structure, including No.1 plate, No. two plates, No. three plates, No. four plates and No. five plates；The present invention provides a kind of aircraft body structures, it is designed using expandable type disjunctor, four side of No.1 plate is hinged four blocks of plates, form agent structure, four blocks of plates correspond to two-by-two, and pass through corresponding clamp card slot and be fixed, installation forming is convenient, without welding machine or rivet, in addition four blocks of hinged plates are provided with flanging, ensure the connection area with covering, and flanging after in body, installation is complete between there are gaps, certain deformation space is provided, the situation that body is delayed to be pressurized and causes covering cracked.
Description
Technical field
The present invention relates to technical field of aircraft structure design, and in particular to a kind of aircraft body structure.
Background technology
Aircraft refers to that the power plant with a tool or more tool engines generates the thrust advanced or pulling force, by consolidating for fuselage
Determine wing and generate lift, in the aircraft for overweighting air of endoatmosphere flight.
Aircraft is one of most great invention early 20th century, and after aircraft invention, aircraft has become modern civilization
The indispensable vehicles.
There are some rectangular body parts on aircraft, these bodies combination forming by the way of welding or riveting mostly is preceding
A kind of mode easily leaves soldering, subsequently also needs to carry out edge polishing, and the latter needs to use rivet punching fixation, needs to set
A kind of novel body structure is counted, it can combination forming without welding or rivet.
Invention content
(1) the technical issues of solving
Present invention aims to overcome that the shortcomings of the prior art, and a kind of aircraft body structure is provided.
(2) technical solution
A kind of aircraft body structure, including No.1 plate, No. two plates, No. three plates, No. four plates and No. five plates；The No.1 plate four
While the base of No. two plates, No. three plates, No. four plates and No. five plates is respectively articulated with by loose-leaf；No. two plates, No. three plates, No. four plates
And the top margin of No. five plates is provided with flanging；No. two plates are symmetrical with No. four plates and structure is identical, No. three plates and No. five plates are symmetrical
And structure is identical；No. three plate two sides are provided with clamp, and clamp end set is fluted, and groove is provided with fixture block, fixture block
Spring is connected with bottom portion of groove, No. two plate side walls are correspondingly arranged on card slot, and card slot corresponds to fixture block and is provided with through-hole.
Preferably, the clamp is uniformly arranged on side.
Preferably, the fixture block section is trapezoidal at a right angle, and right-angle side is parallel with clamp and connecting spring, the high one end of bevel edge
Than low one end closer to corresponding No. three plates or No. five plates.
Preferably, the right-angle side of the fixture block is provided at both ends with protrusion, and groove is corresponding T-slot.
Preferably, for the flanging into isosceles trapezoid, top margin is shorter than base, and top margin connects corresponding No. two plates, No. three plates, four
Number plate or No. five plates, the corresponding interior angle of long side are 50 °~60 °.
Preferably, the slot opening is located inside towards inside, through-hole.
Preferably, the slot opening is located at outside towards outside, through-hole.
(3) advantageous effect
The present invention provides a kind of aircraft body structures, are designed using expandable type disjunctor, and four side of No.1 plate is four pieces hinged
Plate forms agent structure, and four blocks of plates correspond to two-by-two, and pass through corresponding clamp card slot and be fixed, and installation forming is convenient, without
By welding machine or rivet, four blocks of hinged plates are provided with flanging, guarantee and the connection area of covering in addition, and flanging is in body
There are gaps between after installation is complete, provide certain deformation space, the feelings that body is delayed to be pressurized and causes covering cracked
Condition.
Description of the drawings
In order to illustrate the technical solution of the embodiments of the present invention more clearly, embodiment will be described below required
Attached drawing is briefly described, it should be apparent that, the accompanying drawings in the following description is only some embodiments that the present invention protects, for
For those of ordinary skill in the art, without creative efforts, other are can also be obtained according to these attached drawings
Attached drawing.
Fig. 1 is the expanded view of one embodiment of the invention；
Fig. 2 is the expanded view after one embodiment of the invention flanging flattens；
Fig. 3 is the structure chart of No. three plates in Fig. 1；
Fig. 4 is the structure chart of No. two plates in Fig. 1；
Fig. 5 is the structure chart of clamp in the present invention；
Fig. 6 is the structure chart of flanging in the present invention；
Fig. 7 is the installation diagram of one embodiment of the invention；
Fig. 8 is the expanded view of another embodiment of the present invention.
In attached drawing, parts list represented by the reference numerals are as follows：
1- No.1 plates, No. bis- plates of 2-, No. tri- plates of 3-, No. tetra- plates of 4-, No. five plates of 5-, 6- loose-leaves, 7- clamps, 701- fixture blocks,
702- springs, 8- through-holes, 9- flangings.
Specific embodiment
Below in conjunction with the attached drawing in the embodiment of the present invention, the technical solution in the embodiment of the present invention is carried out clear, complete
Site preparation describes, it is clear that described embodiment is only part of the embodiment of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, those of ordinary skill in the art are obtained all other without making creative work
Embodiment shall fall within the protection scope of the present invention.
Referring to attached drawing, a kind of aircraft body structure, including 3, No. four plates 4 of the plate of plate 2, three of No.1 plate 1, two and No. five plates
5；1 four side of No.1 plate is respectively articulated with the base of No. two plate 2, No. three plates, 3, No. four plates 4 and No. five plates 5 by loose-leaf 6；No. two plates 2,
The top margin of 3, No. four plates 4 of No. three plates and No. five plates 5 is machined with flanging 9；No. two plates 2 and No. four plates 4 are symmetrical and structure is identical, No. three
Plate 3 is symmetrical with No. five plates 5 and structure is identical；No. three 3 two sides of plate are connected with clamp 7, and 7 end of clamp processes fluted, groove
Fixture block 701 is provided with, fixture block 701 is connected with spring 702 with bottom portion of groove, and No. two 2 side wall of plate correspondences are machined with card slot, card slot pair
Fixture block 701 is answered to be machined with through-hole 8.
Wherein, clamp 7 is uniformly arranged on side.
Wherein, 701 section of fixture block is trapezoidal at a right angle, and right-angle side is parallel with clamp 7 and connecting spring 702, bevel edge it is high one
End is than low one end closer to corresponding No. three plates 3 or No. five plates 5.
Wherein, the right-angle side both ends of fixture block 701 are machined with protrusion, and groove is corresponding T-slot, effectively prevent fixture block 701
It comes off.
Wherein, for flanging 9 into isosceles trapezoid, top margin is shorter than base, and top margin connects the corresponding plate 3, four of No. two plates 2, three
Plate 4 or No. five plates 5, the corresponding interior angle of long side are 50 °~60 °.
In one embodiment, slot opening is located inside towards inside, through-hole 8.
In another embodiment, slot opening is located at outside towards outside, through-hole 8.
Specifically, No. two plates 4 of plate 3, four of plate 2, three and No. five rotations of plate 5 erect, the clamp 7 of No. three plates 3 is inserted into two
The clamp 7 of number 4, No. five plates 5 of plate 2 and No. four plates is inserted into No. two plates 2 and No. four plates 4, fixture block 701 engage through-hole 8 and complete casket
It is body formed, it is convenient and efficient.Flanging 9 is connected covering and realizes that body is fixed by i.e. available rivet later.
Present invention disclosed above preferred embodiment is only intended to help to illustrate the present invention.There is no detailed for preferred embodiment
All details are described, also do not limit the only specific embodiment of the invention.Obviously, according to the content of this specification, can make
Many modifications and variations.This specification is chosen and specifically describes these embodiments, is in order to preferably explain the original of the present invention
Reason and practical application, so as to which skilled artisan be enable to be best understood by and utilize the present invention.The present invention is only authorized
The limitation of sharp claim and its four corner and equivalent.
Claims (7)
1. a kind of aircraft body structure, it is characterised in that：Including No.1 plate, No. two plates, No. three plates, No. four plates and No. five plates；Institute
State the base that four side of No.1 plate is respectively articulated with No. two plates, No. three plates, No. four plates and No. five plates by loose-leaf；No. two plates, three
The top margin of number plate, No. four plates and No. five plates is provided with flanging；No. two plates are symmetrical with No. four plates and structure is identical, No. three plates with
No. five plate is symmetrical and structure is identical；No. three plate two sides are provided with clamp, and clamp end set is fluted, and groove is provided with
Fixture block, fixture block and bottom portion of groove are connected with spring, and No. two plate side walls are correspondingly arranged on card slot, card slot correspond to fixture block be provided with it is logical
Hole.
2. a kind of aircraft body structure according to claim 1, it is characterised in that：The clamp is uniformly arranged on side
On.
3. a kind of aircraft body structure according to claim 1, it is characterised in that：The fixture block section is trapezoidal at a right angle,
Right-angle side is parallel with clamp and connecting spring, and the high one end of bevel edge is than low one end closer to corresponding No. three plates or No. five plates.
4. a kind of aircraft body structure according to claim 3, it is characterised in that：The right-angle side both ends setting of the fixture block
There is protrusion, groove is corresponding T-slot.
5. a kind of aircraft body structure according to claim 1, it is characterised in that：The flanging is into isosceles trapezoid, top margin
Shorter than base, top margin connect corresponding No. two plates, No. three plates, No. four plates or No. five plates, and the corresponding interior angle of long side is 50 °~60 °.
6. a kind of aircraft body structure according to claim 1, it is characterised in that：The slot opening leads to towards inside
Hole is located inside.
7. a kind of aircraft body structure according to claim 1, it is characterised in that：The slot opening leads to towards outside
Hole is located at outside.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810000635.XA CN108177788B (en) | 2018-01-02 | 2018-01-02 | A kind of aircraft body structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810000635.XA CN108177788B (en) | 2018-01-02 | 2018-01-02 | A kind of aircraft body structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108177788A true CN108177788A (en) | 2018-06-19 |
| CN108177788B CN108177788B (en) | 2018-12-07 |
Family
ID=62549695
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810000635.XA Expired - Fee Related CN108177788B (en) | 2018-01-02 | 2018-01-02 | A kind of aircraft body structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108177788B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020104839A1 (en) * | 2001-02-07 | 2002-08-08 | Szu-Chang Hsiao | Innovation of containing box |
| CN200974632Y (en) * | 2006-11-09 | 2007-11-14 | 张振岳 | Structure improvement for veneer cutlery box |
| CN204181493U (en) * | 2014-08-03 | 2015-03-04 | 于迎春 | Portable oven |
| CN206087677U (en) * | 2016-06-12 | 2017-04-12 | 胡予 | Portable composite receiver |
| CN206332083U (en) * | 2016-12-30 | 2017-07-14 | 芜湖天量电池系统有限公司 | A kind of electrokinetic cell draw box mechanism |
-
2018
- 2018-01-02 CN CN201810000635.XA patent/CN108177788B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020104839A1 (en) * | 2001-02-07 | 2002-08-08 | Szu-Chang Hsiao | Innovation of containing box |
| CN200974632Y (en) * | 2006-11-09 | 2007-11-14 | 张振岳 | Structure improvement for veneer cutlery box |
| CN204181493U (en) * | 2014-08-03 | 2015-03-04 | 于迎春 | Portable oven |
| CN206087677U (en) * | 2016-06-12 | 2017-04-12 | 胡予 | Portable composite receiver |
| CN206332083U (en) * | 2016-12-30 | 2017-07-14 | 芜湖天量电池系统有限公司 | A kind of electrokinetic cell draw box mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108177788B (en) | 2018-12-07 |
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| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| 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: 20181207 Termination date: 20220102 |