CN108032988A - A kind of fibre reinforced composites aircraft bay section connection structure and preparation method thereof - Google Patents
A kind of fibre reinforced composites aircraft bay section connection structure and preparation method thereof Download PDFInfo
- Publication number
- CN108032988A CN108032988A CN201711014578.2A CN201711014578A CN108032988A CN 108032988 A CN108032988 A CN 108032988A CN 201711014578 A CN201711014578 A CN 201711014578A CN 108032988 A CN108032988 A CN 108032988A
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- cell type
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- composite material
- connection structure
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Classifications
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- 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
- B64C1/068—Fuselage sections
- B64C1/069—Joining arrangements therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/345—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using matched moulds
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention discloses a kind of fibre reinforced composites aircraft bay section connection structure and preparation method thereof, belong to aircraft composite structure design field.The connection structure includes two identical composite material case type structures and a high tensile metal bolt；Each composite material case type structures include left side cell type component, middle cell type component, right side cell type component and L-type component；Three cell type components are uniformly distributed successively on L-type component；There is square opening on case type structures vertical panel, open bolt hole on level board, when use is connected two case type structures by spanner metal bolts.Its preparation method uses resin transfer molding technique, and foldable formed four components are coated toughness reinforcing reinforced resin, molded in a mold, and high temperature and pressure cures after injecting glue, in bear after completing.This invention ensures that aircraft connection structure intensity, adds the rigidity of connection structure, effectively reduce stress concentration, connection structure assembly feasibility is improved.
Description
Technical field
The present invention relates to aircraft composite structure design field, more particularly to a kind of fibre reinforced composites to fly
Device bay section connection structure and preparation method thereof.
Background technology
With the continuous development of fibre reinforced composites, its exclusive specific stiffness, intensity are high in addition, corrosion-resistant, anti-tired
The advantages of labor performance is good, fibre reinforced composites are received by every field, especially in aerospace field application
It is the most extensive.Composite material connection design is the key component in composite aircraft structure design, and connection structure is firm
Degree directly influences the security of Flight Vehicle Structure with intensity.
Existing composite material connection structure mainly includes mechanically connecting connecting with being glued, for Flight Vehicle Structure,
It cannot be guaranteed aerodynamic configuration using traditional mechanical connecting structure；Using traditional cementing structure then flexibility is assembled in aircraft
With being difficult to ensure that on bonding quality.Therefore, composite material complex joint structure becomes the mainstream in the connection application of aircraft bay section
Connection structure.
Common composite material complex joint tends to meet flight in existing composite aircraft cargo tank structure
The intensity requirement of device structure, but cannot be guaranteed in rigidity, the flexibility either assembled is restricted or aerodynamic configuration
It can not ensure, or manual manufacture cost is higher, waste of material is than more serious.
The content of the invention
The present invention is a kind of high with the Cost Design of relative moderate in order to overcome the shortcomings of original aircraft bay section connection structure
The composite joint of rigidity, high intensity, there is provided a kind of fibre reinforced composites aircraft bay section connection structure and its system
Preparation Method.
The fibre reinforced composites aircraft bay section connection structure, including two identical composite material cell type knots
Structure and a high tensile metal bolt；By high tensile metal bolt bottom to bottom company symmetrical above and below between two composite material case type structures
Connect；
Each composite material case type structures include：Left side cell type component, middle cell type component, right side cell type component and one
A L-type component；L-type component includes level board and vertical panel；And 2 times that the thickness of level board is vertical plate thickness, level board
Fleece-laying mode is laid with to intersect；
Left side cell type component, middle three cell type components of cell type component and right side cell type component are evenly distributed on L-type successively
On component；
Left side cell type component and right side cell type component are bilateral symmetry, and left side cell type component includes level board, vertically
Plate and right-hand apron；Right side cell type component includes level board, vertical panel and left side baffle；Middle cell type component includes level
Plate, vertical panel and left and right sides baffle；
Left side cell type component, middle three cell type components of cell type component and right side cell type component level board width and L
The level board of type component is of same size, and three cell type components are connected with L-type element joints in transition.
Size is consistent in the vertical panel height of three cell type components, is respectively less than the vertical panel height of L-type component, and and L-type
The vertical panel transition connection of component；
The fixation adjacent with the right-hand apron of left side cell type component of middle cell type left member side side guard, and middle cell type component
The fixation adjacent with the left side baffle of right side cell type component of right side side guard；And four lateral side baffles are identical, each side gear
Plate is each perpendicular to L-type modular level plate, and length and L-type modular level plate are of same size；
On the vertical plate face center line of middle cell type component, leave one while penetrate the square of the vertical panel of L-type component
Opening, the specific size of square opening make choice according to the size of practical flight device, and four angles of square opening are chamfering.
After the shaping of composite material case type structures, a bolt hole, spiral shell are opened on the level board center line of middle cell type component
Keyhole is located on composite material case type structures level board center line.
A kind of preparation method of fibre reinforced composites aircraft bay section connection structure, predominantly composite material cell type knot
The preparation of structure, its manufacturing process use resin transfer molding technique, and specific make step is as follows：
Step 1: male model and master mold are made respectively according to composite material case type structures；
For two composite material case type structures by high tensile metal bolt bottom to bottom connection symmetrical above and below, pass through male model
Mold to obtain whole composite material case type structures with master mold；
In the mould of male model and master mold, changeover portion is left in the junction of three cell type components and L-type component；And male model
Middle cell type component and L-type component on vertical panel on leave square protruding, serve as core, support among cell type component it is vertical
Square opening on plate.
Or square protruding is not left on middle the cell type component and L-type component of male model, wait composite material case type structures
After completing, square opening is carried out on the vertical panel on middle cell type component and L-type component manually.
Step 2: left side cell type component, middle cell type component and right side cell type component and L-type component are rolled over dry fibers
Build up type.
In the folding process of L-type component, level board will take the mode intersected and be laid with.
Step 3: on foldable formed left side cell type component, middle cell type component, right side cell type component and L-type component
Coat toughness reinforcing reinforced resin.
Step 4: by preforming left side cell type component, middle cell type component, right side cell type component and L-type component according to
Drawing is bonded, and is put into the molding male model of making and master mold mould and is molded, is then noted by hole for injecting glue into mould
Glue, case type structures are formed by curing finally by high temperature and pressure.
Step 5: after composite material case type structures complete, one is opened on the horizonal base plate of composite material case type structures
A bolt hole；
Step 6: completed in connection in use, being prepared two with high tensile metal bolt by spanner on the outside of aircraft
Composite material case type structures symmetrically connect, to realize the connection of aircraft.
Advantages of the present invention and the beneficial effect brought are：
(1) a kind of fibre reinforced composites aircraft bay section connection structure of the present invention, adds L-type using three cell type components
Component forms composite material case type structures, relative to traditional L-type connection structure, effectively increases the rigidity of structure；In L-type component
Transition is set with three cell type element joints, effectively reduces stress concentration.
(2) a kind of fibre reinforced composites aircraft bay section connection structure of the present invention, composite material case type structures can be with
It is integrally formed with aircraft cargo tank structure, relative to traditional metal transfer structure, improves the integrality of structure, reduction finishes
Structure weight.
(3) a kind of fibre reinforced composites aircraft bay section connection structure of the present invention, connecting pin design is in side, application
In Flight Vehicle Structure, the aerodynamic configuration of aircraft ensure that.
(4) a kind of preparation method of fibre reinforced composites aircraft bay section connection structure of the present invention, L-type modular level
Laying is 2 times of vertical laying using laying, design thickness is intersected, and adds the rigidity of connection structure.
(5) a kind of preparation method of fibre reinforced composites aircraft bay section connection structure of the present invention, composite wood magazine
Type structure leaves square opening in vertical panel, and chamfering is left in opening, ensure that the feasibility of connection structure assembling, at the same time
Avoid the stress concentration of opening.
Brief description of the drawings
Fig. 1 is the schematic diagram of fibre reinforced composites aircraft bay section connection structure of the present invention；
Fig. 2 is composite material case type structures assembling schematic diagram of the present invention；
Fig. 3 is composite element assembly schematic diagram of the present invention；
Fig. 4 is the composite material case type structures partial elevation view of the present invention；
Fig. 5 is the composite material case type structures partial side view of the present invention.
Fig. 6 is the flow chart of fibre reinforced composites aircraft bay section connection structure preparation method of the present invention.
In figure：
1- composite material case type structures；2- high tensile metal bolts；
11-L type components；12- cell type components；13- square openings；14- changeover portions；15- filling regions；
111-L type modular level plates；112-L type component vertical panels；
Cell type component on the left of 121-；Cell type component among 122-；Cell type component on the right side of 123-；
131- chamferings.
Embodiment
Elaborate with reference to the accompanying drawings and examples to the present invention.
A kind of fibre reinforced composites aircraft bay section connection structure, as shown in Figure 1, including a pair of of composite material cell type
Structure 1 and a high tensile metal bolt 2, two composite material case type structures 1 in bottom to bottom by high tensile metal bolt about 2 it is right
Claim connection.The present embodiment is attached guided missile, rocket bay section using 8 connection structures.
As shown in Fig. 2, each composite material case type structures 1 include cell type component 12 and L-type component 11, and in curing
It is preceding dry fibers as shown in Figure 3 by way of make shaping, then carry out assembled co-curing.
As shown in figure 4, cell type component 12 includes left side cell type component 121, middle cell type component 122 and right side cell type component
123, and three cell type components leave changeover portion 14 at the longitudinally connected place with L-type component 11, add L using three cell type components
Type component forms composite material case type structures, adds the rigidity of connection structure.
As shown in figure 5, L-type component 11 includes level board 111 and vertical panel 112,111 thickness of level board is vertical panel 112
2 times of thickness, and the fleece-laying mode of level board 111 is laid with to intersect.
Three cell type components are evenly distributed on L-type component successively；Left side cell type component 121 and right side cell type component 123
For bilateral symmetry, left side cell type component 121 includes level board, vertical panel and right-hand apron；Right side cell type component 123 wraps
Include level board, vertical panel and left side baffle；Middle cell type component 122 includes level board, vertical panel and left and right sides baffle；
The level board of left side cell type component 121, middle cell type component 122 and right side 123 3 cell type components of cell type component
Width is of same size with the level board 111 of L-type component, and three cell type components and 11 junction of L-type component are in transition
Connection.
The vertical board size of three cell type components is consistent, middle 122 left side side guard of cell type component and left side cell type component
The 121 adjacent fixation of right-hand apron, and the left side baffle of middle 122 right side side guard of cell type component and right side cell type component 123
Adjacent fixation；And four lateral side baffles are identical, each lateral side baffle is each perpendicular to L-type modular level plate 111, and length with
L-type modular level plate 111 is of same size；
A square opening 13 for penetrating 11 vertical panel of L-type component is left on the vertical panel of middle cell type component 122.Square is opened
Mouth 13 is located at the vertical panel bottom centre of middle cell type component 122, and specific size makes choice according to the size of practical flight device.
There is the chamfering 131 that radius is 3mm at four angles of square opening 13, ensure that the feasibility of connection structure assembling, avoid at the same time
The stress concentration of opening.
After the shaping of composite material case type structures, a bolt hole is opened on the level board center line of middle cell type component 122,
The well format is unthreaded hole, and distance of the position of bolt hole away from composite material case type structures vertical panel is about the 2/ of horizonal base plate width
5, and on centerline, while structural strength is ensured, it is ensured that the rigidity of structure is big.
Composite material case type structures preparation method is made of resin transfer molding technique, as shown in fig. 6, its step
It is specific as follows：
Step 1: case type structures mould is made according to the structure type feature of composite material case type structures；
In whole cell type element mold, changeover portion is left in the junction of three cell type components and L-type component；Male model
Square protruding is left on middle cell type component and L-type component, serves as core, supports the square of middle 122 vertical panel of cell type component
Opening；
First preprocessing square opening and directly evolution type opening two schemes after processing are all feasible in manufacturing process.
Step 2: by left side cell type component 121,11 folding of middle cell type component 122, right side cell type component 123 and L-type component
Build up type；
As shown in Figure 3, three cell type components make of dry fibers and are molded, and with dry fibers fill area at interconnection
Domain 15, concrete form is as shown in Figure 4；Level board 111 will take the side for intersecting and being laid with wherein in the folding process of L-type component 11
Formula；
Step 3: in foldable formed left side cell type component 121, middle cell type component 122 and right side cell type component 123 with
And toughness reinforcing reinforced resin is coated on L-type component 11, become preforming each component.
Step 4: by preforming left side cell type component 121, middle cell type component 122, right side cell type component 123 and L-type
Component 11 is bonded according to drawing, is put into make in molding case type structures mould and is molded, then by hole for injecting glue to
Injecting glue in case type structures mould, case type structures are formed by curing finally by high temperature and pressure.
Step 5: after case type structures complete, a bolt hole is opened on the horizonal base plate of composite material case type structures；
Step 6: completed in connection in use, being prepared two with high tensile metal bolt by spanner on the outside of aircraft
Composite material case type structures symmetrically connect, to realize the connection of aircraft.
The fibre reinforced composites aircraft bay section connection structure of the present invention adds L-type component by three cell type components
Design, and 2 times of the design that L-type modular level overlay thickness is vertical laying, collective effect, effectively increase this connection knot
The rigidity of structure.The connection structure is applied in Flight Vehicle Structure, effectively reduces stress concentration, ensure that the gas of aircraft
Dynamic shape.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all essences in the present invention
All any modification, equivalent and improvement made within refreshing and principle etc., should all be included in the protection scope of the present invention.
Claims (6)
1. a kind of fibre reinforced composites aircraft bay section connection structure, it is characterised in that including two identical composite woods
Expect case type structures and a high tensile metal bolt；By high tensile metal bolt bottom on bottom between two composite material case type structures
Lower symmetrical connection；
Each composite material case type structures include：Left side cell type component, middle cell type component, right side cell type component and a L
Type component；L-type component includes level board and vertical panel；And 2 times that the thickness of level board is vertical plate thickness；
Left side cell type component, middle three cell type components of cell type component and right side cell type component are evenly distributed on L-type component successively
On；
Left side cell type component and right side cell type component are bilateral symmetry, and left side cell type component includes level board, vertical panel with
And right-hand apron；Right side cell type component includes level board, vertical panel and left side baffle；Middle cell type component includes level board,
Vertical panel and left and right sides baffle；
Left side cell type component, middle three cell type components of cell type component and right side cell type component level board width with L-type structure
The level board of part is of same size；Size is consistent in the vertical panel height of three cell type components, is respectively less than the vertical panel of L-type component
Highly；
The fixation adjacent with the right-hand apron of left side cell type component of middle cell type left member side side guard, and middle cell type right member side
Side guard fixation adjacent with the left side baffle of right side cell type component；And four lateral side baffles are identical, each lateral side baffle is equal
Perpendicular to L-type modular level plate, and length and L-type modular level plate are of same size；
On the vertical plate face center line of middle cell type component, leave one while penetrate the square opening of the vertical panel of L-type component,
The specific size of square opening makes choice according to the size of practical flight device, and four angles of square opening are chamfering；
After the shaping of composite material case type structures, a bolt hole, bolt hole are opened on the level board center line of middle cell type component
On composite material case type structures level board center line.
2. a kind of fibre reinforced composites aircraft bay section connection structure as claimed in claim 1, it is characterised in that described
Three cell type components be connected with L-type element joints in transition.
3. a kind of fibre reinforced composites aircraft bay section connection structure as claimed in claim 1, it is characterised in that described
The radius of chamfering be 3mm.
4. a kind of fibre reinforced composites aircraft bay section connection structure as claimed in claim 1, it is characterised in that described
Distance of the position of bolt hole away from composite material case type structures vertical panel center line be level board width 2/5.
5. preparing a kind of method of fibre reinforced composites aircraft bay section connection structure as claimed in claim 1, it is special
Sign is that its manufacturing process uses resin transfer molding technique, and specific make step is as follows：
Step 1: male model and master mold are made respectively according to composite material case type structures；
For two composite material case type structures by high tensile metal bolt bottom to bottom connection symmetrical above and below, pass through male model and mother
Mould molds to obtain whole composite material case type structures；
Step 2: with dry fibers by left side cell type component, middle cell type component and right side cell type component and L-type elements fold into
Type；
In the folding process of L-type component, the fleece-laying mode of level board is laid with to intersect；
Step 3: coated on foldable formed left side cell type component, middle cell type component, right side cell type component and L-type component
Toughness reinforcing reinforced resin；
Step 4: by preforming left side cell type component, middle cell type component, right side cell type component and L-type component according to drawing
Be bonded, be put into make in molding male model and master mold mould and molded, then by hole for injecting glue into mould injecting glue, most
Case type structures are formed by curing by high temperature and pressure afterwards；
Step 5: after composite material case type structures complete, a spiral shell is opened on the horizonal base plate of composite material case type structures
Keyhole；
Step 6: in connection in use, preparing answering for completion by two by spanner high tensile metal bolt on the outside of aircraft
Condensation material case type structures symmetrically connect, to realize the connection of aircraft.
6. a kind of preparation method of fibre reinforced composites aircraft bay section connection structure as claimed in claim 5, it is special
Sign is, in step 1, leaves square protruding on the vertical panel on middle the cell type component and L-type component of the male model, fills
Work as core, support the square opening on middle cell type component vertical panel；Or on middle the cell type component and L-type component of male model
Square protruding is not left, it is vertical on middle cell type component and L-type component manually after composite material case type structures complete
Square opening is carried out in straight panel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711014578.2A CN108032988B (en) | 2017-10-25 | 2017-10-25 | Fiber reinforced composite aircraft cabin connecting structure and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711014578.2A CN108032988B (en) | 2017-10-25 | 2017-10-25 | Fiber reinforced composite aircraft cabin connecting structure and preparation method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108032988A true CN108032988A (en) | 2018-05-15 |
| CN108032988B CN108032988B (en) | 2020-06-16 |
Family
ID=62092583
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711014578.2A Active CN108032988B (en) | 2017-10-25 | 2017-10-25 | Fiber reinforced composite aircraft cabin connecting structure and preparation method thereof |
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| CN101758923A (en) * | 2008-12-25 | 2010-06-30 | 西安飞机工业（集团）有限责任公司 | Composite material box-shaped rib and manufacturing method thereof |
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| CN105235888A (en) * | 2014-07-08 | 2016-01-13 | 空中客车营运有限公司 | Structure |
| CN105438438A (en) * | 2014-09-17 | 2016-03-30 | 波音公司 | Wing edge attachment of composite materials and method thereof |
| CN106314759A (en) * | 2016-09-06 | 2017-01-11 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Spar connecting structure of aircraft wing |
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2017
- 2017-10-25 CN CN201711014578.2A patent/CN108032988B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120223183A1 (en) * | 2005-06-28 | 2012-09-06 | Hexcel Corporation | Aerospace articles made from quasi-isotropic chopped prepreg |
| CN101873965A (en) * | 2007-10-18 | 2010-10-27 | 空中客车运营简易股份公司 | The splicing of the Ω shape reinforcing member at place, airframe ring week junction surface |
| CN101758923A (en) * | 2008-12-25 | 2010-06-30 | 西安飞机工业（集团）有限责任公司 | Composite material box-shaped rib and manufacturing method thereof |
| CN105235888A (en) * | 2014-07-08 | 2016-01-13 | 空中客车营运有限公司 | Structure |
| CN105438438A (en) * | 2014-09-17 | 2016-03-30 | 波音公司 | Wing edge attachment of composite materials and method thereof |
| CN104552977A (en) * | 2014-12-15 | 2015-04-29 | 湖北三江航天红阳机电有限公司 | Segmented molding method of thermal protection layer of combined cabin |
| CN106314759A (en) * | 2016-09-06 | 2017-01-11 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Spar connecting structure of aircraft wing |
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| Publication number | Publication date |
|---|---|
| CN108032988B (en) | 2020-06-16 |
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