CN107054615A - A kind of aircraft body structure - Google Patents
A kind of aircraft body structure Download PDFInfo
- Publication number
- CN107054615A CN107054615A CN201710200446.2A CN201710200446A CN107054615A CN 107054615 A CN107054615 A CN 107054615A CN 201710200446 A CN201710200446 A CN 201710200446A CN 107054615 A CN107054615 A CN 107054615A
- Authority
- CN
- China
- Prior art keywords
- flange
- aircraft
- covering
- stiffening plate
- present
- 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.)
- Pending
Links
- 239000007787 solid Substances 0.000 claims 1
- 208000037656 Respiratory Sounds Diseases 0.000 abstract description 7
- 239000002184 metal Substances 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000007373 indentation Methods 0.000 description 1
- 238000009434 installation Methods 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
- 230000002787 reinforcement Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- 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
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D2045/0065—Black boxes, devices automatically broadcasting distress signals
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses a kind of aircraft body structure, belong to technical field of aircraft structure design.The main flange (2) for including body body (1) and being arranged on body body (1) end, body body (1) is connected at covering (3) opening by the flange (2), the flange (2) sets jagged in itself and body body (1) junction, stiffening plate (4) is provided between two adjacent flange, the stiffening plate (4) is fixed on the covering (3).The present invention effectively reduces the tear problem that aircraft body is caused at flared end portions to covering by the design of stiffening plate and the design of breach, reduces the probability of crackle appearance.
Description
Technical field
The invention belongs to technical field of aircraft structure design, and in particular to a kind of aircraft body structure.
Background technology
There are some square body parts on aircraft, body is arranged on the covering of aircraft surfaces in interior of aircraft, due to
The effect of load that body is subject to, easily causes near body opening with covering junction and crackle occurs, in body and covering
On crackle can all occur, had a strong impact on the service life of body.
The content of the invention
In order to solve the above problems, the present invention proposes a kind of aircraft body structure, including body body and is arranged on
The flange of body body end, body body is connected at covering opening by the flange, and the flange is in itself and body sheet
Body junction sets jagged, is provided with stiffening plate between two adjacent flange, the stiffening plate is fixed on the covering
On.
Preferably, the breach is that a quarter is circular.
In such scheme preferably, the circular radius is 5~20mm.
In such scheme preferably, the body body is made up of two pieces of rectangular plates, one of rectangular plate folding
Three faces of body body are built up, another piece of rectangular plate constitutes the 4th face of body body, and the 4th face is fixed and closed
The groove being made up of foregoing three faces.
In such scheme preferably, two pieces of rectangular plates are sheet metal component.
In such scheme preferably, two sheet metal component rivetings.
In such scheme preferably, the flange is welded with the covering.
Body is installed with the method, has saved part manufacturing cost, has reduced inside parts stress, breach round-corner transition
Design (reserved opening) reduces the probability for crackle occur, improves the service life of body structure.
Brief description of the drawings
Fig. 1 is the structural representation of a preferred embodiment of aircraft body structure of the present invention.
Fig. 2 is the aircraft body structure and covering connection diagram of embodiment illustrated in fig. 1 of the present invention.
Wherein, 1 is body body, and 2 be flange, and 3 be covering, and 4 be stiffening plate, and 5 be breach.
Embodiment
To make the purpose, technical scheme and advantage of the invention implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Embodiments of the invention are described in detail with reference to accompanying drawing for face.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, is for only for ease of the description present invention and simplifies description, rather than indicate or imply signified dress
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to present invention protection
The limitation of scope.
The present invention proposes a kind of aircraft body structure, as shown in Figures 1 and 2, mainly includes body body 1 and sets
Flange 2 in the end of body body 1, body body 1 is connected at the opening of covering 3 by the flange 2, and the flange 2 is at it
Set with the junction of body body 1 and stiffening plate 4 is provided between jagged 5, two adjacent flange, the stiffening plate 4 is consolidated
It is scheduled on the covering 3.
Fig. 2 gives the aircraft body structure in the structure with the junction of covering 3, figure, and most middle square is casket
Intracoelomic cavity, be centered around the square surrounding for flange 2 and stiffening plate 4, further illustrate, body inner chamber is (in the middle of in figure
Square) include four side plates, each outside 90 ° of upsets of side plate constitute four flange 2, and any flange is set at the two ends of turn-line
It is equipped with breach, the present embodiment, the breach is that a quarter is circular (90 °), similarly, and the flange adjacent with the flange also has four
/ mono- circular breach, adds the 90 ° of circumferential notches opened in the present embodiment stiffening plate corresponding position, together constitutes
270 ° of circumferential notch.Flange in the present embodiment above Fig. 2 does not remove side redundance, therefore without stiffening plate at this,
Meanwhile, 180 ° of breach are provided with to the position contacted on the flange with the indentation, there of adjacent flange, with polishing not with stiffening plate band
The defect come.
In the present embodiment, the circular radius is 5~20mm.I.e. Zone R round-corner transition is designed and sized to 5~20mm, effectively
The tear problem that aircraft body is caused at flared end portions to covering is reduced, the probability of crackle appearance is reduced.
In the present embodiment, why Fig. 2 is only provided with two reinforcement in the lower section of body inner chamber (intermediate square in figure)
Plate 4, and it is not also provided with stiffening plate 4 above it, it is to be made up of because of body body described in the present embodiment two pieces of rectangular plates,
One of rectangular plate is folded into three faces (intermediate square left side in figure, right side, the line correspondence of downside three of body body
Body body side), another piece of rectangular plate constitutes the 4th face (side line pair in intermediate square in figure of body body
The side for the body body answered), the groove being made up of foregoing three faces is fixed and closed in the 4th face.
In the present embodiment, two pieces of rectangular plates are sheet metal component, and two sheet metal components rivetings.Specifically, sheet material two described later
Side is overturn, and is riveted in two plate faces of the foregoing sheet material being in contact with it.
The body that the present embodiment is installed, has saved part manufacturing cost, reduces inside parts stress, Zone R fillet mistake
The design (reserved opening) crossed reduces the probability for crackle occur, improves the service life of body structure.
Aircraft body structure shown in the invention is carried out aboard, airframe both sides be mounted with altogether two groups this
Body is planted, after installation, the probability for crackle occur have dropped 80%, and service life extends more than 20 times.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
The present invention is described in detail with reference to the foregoing embodiments for pipe, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, the essence of appropriate technical solution is departed from the essence of various embodiments of the present invention technical scheme
God and scope.
Claims (5)
1. a kind of aircraft body structure, it is characterised in that：Mainly include body body (1) and be arranged on body body (1) end
The flange (2) in portion, body body (1) is connected at covering (3) opening by the flange (2), and the flange (2) is in itself and casket
Body body (1) junction sets jagged, and stiffening plate (4) is provided between two adjacent flange, and the stiffening plate (4) is solid
It is scheduled on the covering (3).
2. aircraft body structure as claimed in claim 1, it is characterised in that：The breach is that a quarter is circular.
3. aircraft body structure as claimed in claim 2, it is characterised in that：The circular radius is 5~20mm.
4. aircraft body structure as claimed in claim 1, it is characterised in that：The body body (1) is by two pieces of rectangular plates
Constitute, one of rectangular plate is folded into three faces of body body (1), another piece of rectangular plate constitutes body body (1)
The 4th face, the groove being made up of foregoing three faces is fixed and closed in the 4th face.
5. aircraft body structure as claimed in claim 1, it is characterised in that：The flange is welded with the covering.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710200446.2A CN107054615A (en) | 2017-03-30 | 2017-03-30 | A kind of aircraft body structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710200446.2A CN107054615A (en) | 2017-03-30 | 2017-03-30 | A kind of aircraft body structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107054615A true CN107054615A (en) | 2017-08-18 |
Family
ID=59601385
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710200446.2A Pending CN107054615A (en) | 2017-03-30 | 2017-03-30 | A kind of aircraft body structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107054615A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114526161A (en) * | 2022-04-22 | 2022-05-24 | 成都中科翼能科技有限公司 | Gas turbine's intermediary machine casket and reinforcement structure thereof |
-
2017
- 2017-03-30 CN CN201710200446.2A patent/CN107054615A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114526161A (en) * | 2022-04-22 | 2022-05-24 | 成都中科翼能科技有限公司 | Gas turbine's intermediary machine casket and reinforcement structure thereof |
| CN114526161B (en) * | 2022-04-22 | 2022-07-08 | 成都中科翼能科技有限公司 | Gas turbine's intermediary machine casket and reinforcement structure thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170818 |