CN108032988B - Fiber reinforced composite aircraft cabin connecting structure and preparation method thereof - Google Patents
Fiber reinforced composite aircraft cabin connecting structure and preparation method thereof Download PDFInfo
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- CN108032988B CN108032988B CN201711014578.2A CN201711014578A CN108032988B CN 108032988 B CN108032988 B CN 108032988B CN 201711014578 A CN201711014578 A CN 201711014578A CN 108032988 B CN108032988 B CN 108032988B
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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
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- 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
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- 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
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- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Aviation & Aerospace Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Connection Of Plates (AREA)
Abstract
The invention discloses a fiber reinforced composite aircraft cabin section connecting structure and a preparation method thereof, and belongs to the field of aircraft composite structure design. The connecting structure comprises two identical composite material box-shaped structures and a high-strength metal bolt; each composite box structure comprises a left box member, a middle box member, a right box member and an L-shaped member; the three box-shaped components are sequentially and uniformly distributed on the L-shaped component; the box-shaped structure vertical plate is provided with a square opening, the horizontal plate is provided with a bolt hole, and the two box-shaped structures are connected by a metal bolt through a spanner when the box-shaped structure vertical plate is used. The preparation method adopts a resin transfer molding process, four folded and formed components are coated with toughening and reinforcing resin, the components are closed in a mold, the components are cured at high temperature and high pressure after glue injection, and holes are punched at the bottom after the preparation is finished. The invention ensures the strength of the aircraft connecting structure, increases the rigidity of the connecting structure, effectively reduces stress concentration and improves the assembling feasibility of the connecting structure.
Description
Technical Field
The invention relates to the field of aircraft composite material structure design, in particular to a fiber reinforced composite material aircraft cabin section connecting structure and a preparation method thereof.
Background
With the continuous development of fiber reinforced composite materials and the unique advantages of high specific stiffness, high strength, good corrosion resistance and good fatigue resistance, the fiber reinforced composite materials have been accepted in various fields, and are most widely applied in the aerospace field in particular. The composite material connection design is a key part in the design of the composite material aircraft structure, and the rigidity and the strength of the connection structure directly influence the safety of the aircraft structure.
The existing composite material connecting structure mainly comprises mechanical connection and adhesive connection, and for an aircraft structure, the pneumatic appearance cannot be ensured by using the traditional mechanical connecting structure; the use of conventional glued structures is difficult to guarantee in terms of aircraft assembly flexibility and gluing quality. Accordingly, composite material complex joint configurations are configured as mainstream connection structures in aircraft cabin connection applications.
The common composite material complex joint in the existing composite material aircraft cabin section structure can often meet the strength requirement of the aircraft structure, but the rigidity cannot be ensured, or the assembly flexibility is limited, or the pneumatic appearance cannot be ensured, or the manual manufacturing cost is high, and the material waste is serious.
Disclosure of Invention
The invention provides a cabin section connecting structure of a fiber reinforced composite aircraft and a preparation method thereof, aiming at overcoming the defects of the cabin section connecting structure of the original aircraft and designing a composite material joint with high rigidity and high strength at relatively low cost.
The fiber reinforced composite aircraft cabin section connecting structure comprises two identical composite box-shaped structures and a high-strength metal bolt; the two composite material box-shaped structures are symmetrically connected from bottom to top through high-strength metal bolts;
each composite box-type structure comprises: a left box member, a middle box member, a right box member, and an L-shaped member; the L-shaped component comprises a horizontal plate and a vertical plate; the thickness of the horizontal plate is 2 times of that of the vertical plate, and the fiber laying mode of the horizontal plate is cross laying;
the left box-shaped component, the middle box-shaped component and the right box-shaped component are sequentially and uniformly distributed on the L-shaped component;
the left box-shaped component and the right box-shaped component are in a bilateral symmetry structure, and the left box-shaped component comprises a horizontal plate, a vertical plate and a right baffle; the right box-shaped component comprises a horizontal plate, a vertical plate and a left baffle; the middle box-shaped component comprises a horizontal plate, a vertical plate and a left baffle and a right baffle;
the horizontal plate width of the three box-shaped components of the left box-shaped component, the middle box-shaped component and the right box-shaped component is the same as that of the horizontal plate of the L-shaped component, and the joints of the three box-shaped components and the L-shaped component are in transition connection.
The vertical plates of the three box-shaped components have the same height, are smaller than the height of the vertical plate of the L-shaped component, and are in transitional connection with the vertical plate of the L-shaped component;
the left side baffle of the middle box-shaped component is adjacently fixed with the right side baffle of the left box-shaped component, and the right side baffle of the middle box-shaped component is adjacently fixed with the left side baffle of the right box-shaped component; the four side baffles are completely the same, each side baffle is perpendicular to the L-shaped component horizontal plate, and the length of each side baffle is the same as the width of the L-shaped component horizontal plate;
and a square opening which penetrates through the vertical plate of the L-shaped component at the same time is reserved on the central line of the vertical plate surface of the middle box-shaped component, the specific size of the square opening is selected according to the size of the actual aircraft, and four corners of the square opening are chamfers.
After the composite box-shaped structure is formed, a bolt hole is formed in the center line of the horizontal plate of the middle box-shaped component, and the bolt hole is located in the center line of the horizontal plate of the composite box-shaped structure.
A preparation method of a fiber reinforced composite aircraft cabin section connecting structure mainly comprises the preparation of a composite box-shaped structure, wherein a resin transfer molding forming process is adopted in the preparation process, and the preparation method comprises the following specific preparation steps:
step one, respectively manufacturing a male die and a female die according to a composite material box-shaped structure;
aiming at two composite material box-shaped structures which are symmetrically connected from top to bottom through the bottom of the high-strength metal bolt, the whole composite material box-shaped structure is obtained by matching a male die and a female die;
in the dies of the male die and the female die, transition sections are reserved at the joints of the three box-shaped members and the L-shaped member; and square bulges are left on the middle box-shaped component of the male die and the vertical plate on the L-shaped component and are used as cores for supporting square openings on the vertical plate of the middle box-shaped component.
Or square bulges are not left on the middle box-shaped component and the L-shaped component of the male die, and after the composite material box-shaped structure is manufactured, square openings are manually formed in the vertical plates on the middle box-shaped component and the L-shaped component.
And step two, folding and molding the left box-shaped member, the middle box-shaped member, the right box-shaped member and the L-shaped member by using dry fibers.
During the folding process of the L-shaped member, the horizontal plates are in a cross laying mode.
And step three, coating toughening and reinforcing resin on the left box-shaped member, the middle box-shaped member, the right box-shaped member and the L-shaped member which are formed by folding.
And step four, bonding the preformed left box-shaped component, the middle box-shaped component, the right box-shaped component and the L-shaped component according to a drawing, putting the bonded components into a male die and a female die for die assembly, injecting glue into the dies through glue injection holes, and finally curing at high temperature and high pressure to form a box-shaped structure.
Step five, after the composite material box-shaped structure is manufactured, a bolt hole is formed in a horizontal bottom plate of the composite material box-shaped structure;
and step six, when the composite material box-shaped structure is connected for use, the two prepared composite material box-shaped structures are symmetrically connected through a spanner by using a high-strength metal bolt, so that the connection of the aircrafts is realized.
The invention has the advantages and beneficial effects that:
(1) according to the cabin section connecting structure of the fiber reinforced composite aircraft, the three box-shaped components and the L-shaped component are adopted to form the composite box-shaped structure, so that compared with the traditional L-shaped connecting structure, the structural rigidity is effectively improved; the transition is arranged at the joint of the L-shaped member and the three box-shaped members, so that the stress concentration is effectively reduced.
(2) According to the fiber reinforced composite aircraft cabin section connecting structure, the composite box-shaped structure can be integrally formed with the aircraft cabin section structure, and compared with a traditional metal transition structure, the fiber reinforced composite aircraft cabin section connecting structure has the advantages that the structural integrity is improved, and the structural weight is reduced.
(3) According to the aircraft cabin section connecting structure made of the fiber reinforced composite material, the connecting end is designed on one side and is applied to the aircraft structure, so that the aerodynamic appearance of the aircraft is guaranteed.
(4) According to the preparation method of the fiber reinforced composite material aircraft cabin section connecting structure, the L-shaped component horizontal laying layer is cross laid, the design thickness is 2 times of that of the vertical laying layer, and the rigidity of the connecting structure is increased.
(5) According to the preparation method of the cabin section connecting structure of the fiber reinforced composite aircraft, the square opening is reserved on the vertical plate of the box-shaped structure of the composite material, and the chamfer angle is reserved on the opening, so that the assembling feasibility of the connecting structure is ensured, and the stress concentration at the opening is avoided.
Drawings
FIG. 1 is a schematic view of a fiber-reinforced composite aircraft cabin connection structure of the present invention;
FIG. 2 is an assembled schematic view of a composite box-type structure of the present invention;
FIG. 3 is a schematic illustration of the assembly of the composite member of the present invention;
FIG. 4 is a partial front view of a composite box-type structure of the present invention;
FIG. 5 is a partial side view of a composite box structure of the present invention.
FIG. 6 is a flow chart of a method for manufacturing a fiber reinforced composite aircraft cabin connection structure according to the present invention.
In the figure:
1-composite box-type structure; 2-high strength metal bolts;
an 11-L shaped member; 12-a box-type member; 13-square opening; 14-a transition section; 15-filling the area;
a 111-L member horizontal plate; 112-L-shaped member vertical plates;
121-left box member; 122-middle box type member; 123-right box-type member;
131-chamfering.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
A fiber reinforced composite aircraft cabin section connecting structure is shown in figure 1 and comprises a pair of composite box-shaped structures 1 and a high-strength metal bolt 2, wherein the two composite box-shaped structures 1 are connected in a bottom-to-bottom mode and are in up-and-down symmetrical arrangement through the high-strength metal bolt 2. In the embodiment, 8 connecting structures are adopted to connect missile and rocket cabin sections.
As shown in fig. 2, each composite box structure 1 comprises a box member 12 and an L-shaped member 11, and is formed by dry fibers in the manner shown in fig. 3 before curing, and then is assembled and co-cured.
As shown in fig. 4, the box-shaped members 12 include a left box-shaped member 121, a middle box-shaped member 122 and a right box-shaped member 123, and the transition sections 14 are left at the longitudinal joints of the three box-shaped members and the L-shaped member 11, and the three box-shaped members and the L-shaped member are used to form a composite box-shaped structure, so that the rigidity of the connecting structure is increased.
As shown in fig. 5, the L-shaped member 11 includes a horizontal plate 111 and a vertical plate 112, the horizontal plate 111 has a thickness 2 times that of the vertical plate 112, and the horizontal plate 111 is laid with fibers in a crossing manner.
The three box-shaped components are sequentially and uniformly distributed on the L-shaped component; the left box-shaped member 121 and the right box-shaped member 123 are of a left-right symmetrical structure, and the left box-shaped member 121 comprises a horizontal plate, a vertical plate and a right baffle; the right box-shaped member 123 includes a horizontal plate, a vertical plate, and a left baffle; the middle box-shaped member 122 includes a horizontal plate, a vertical plate, and left and right side baffle plates;
the horizontal plate width of the left box-shaped member 121, the middle box-shaped member 122 and the right box-shaped member 123 is the same as the width of the horizontal plate 111 of the L-shaped member, and the three box-shaped members are connected with the L-shaped member 11 in a transition manner.
The vertical plates of the three box-shaped members are consistent in size, the left side baffle of the middle box-shaped member 122 is adjacently fixed with the right side baffle of the left box-shaped member 121, and the right side baffle of the middle box-shaped member 122 is adjacently fixed with the left side baffle of the right box-shaped member 123; the four side baffles are completely the same, each side baffle is perpendicular to the L-shaped component horizontal plate 111, and the length of each side baffle is the same as the width of the L-shaped component horizontal plate 111;
the vertical plate of the middle box-shaped member 122 is provided with a square opening 13 which penetrates the vertical plate of the L-shaped member 11. The square opening 13 is located in the center of the bottom of the vertical plate of the middle box-shaped member 122, and the specific size is selected according to the size of the actual aircraft. Four corners of the square opening 13 are provided with chamfers 131 with the radius of 3mm, so that the feasibility of assembling the connecting structure is ensured, and meanwhile, the stress concentration at the opening is avoided.
After the composite box structure is formed, a bolt hole in the form of a light hole is formed in the center line of the horizontal plate of the middle box member 122, the bolt hole is located at a distance of about 2/5 of the width of the horizontal bottom plate from the vertical plate of the composite box structure, and the structural rigidity is ensured on the center line while the structural strength is ensured.
The preparation method of the composite material box-shaped structure adopts a resin transfer molding forming process, as shown in fig. 6, the steps are as follows:
firstly, manufacturing a box-shaped structure mold according to the structural form characteristics of a composite material box-shaped structure;
in the whole box-shaped member mould, transition sections are reserved at the joints of the three box-shaped members and the L-shaped member; square bulges are left on the middle box-shaped component and the L-shaped component of the male die and are used as cores for supporting square openings of the vertical plate of the middle box-shaped component 122;
in the manufacturing process, two schemes of pre-processing the square opening and directly processing the square opening after processing are available.
Step two, folding and forming the left box-shaped member 121, the middle box-shaped member 122, the right box-shaped member 123 and the L-shaped member 11;
as shown in fig. 3, three box members are formed from dry fibres and the regions 15 are filled with dry fibres at the interconnection, in the form shown in fig. 4; wherein the horizontal plate 111 is in a cross laying mode in the folding process of the L-shaped member 11;
and step three, coating toughening and reinforcing resin on the left box-shaped member 121, the middle box-shaped member 122, the right box-shaped member 123 and the L-shaped member 11 which are formed by folding, and forming the preformed components.
And step four, bonding the preformed left box-shaped component 121, the middle box-shaped component 122, the right box-shaped component 123 and the L-shaped component 11 according to a drawing, putting the bonded components into a molded box-shaped structure mold for mold assembly, injecting glue into the box-shaped structure mold through glue injection holes, and finally curing at high temperature and high pressure to form a box-shaped structure.
Step five, after the box-shaped structure is manufactured, a bolt hole is formed in a horizontal bottom plate of the composite material box-shaped structure;
and step six, when the composite material box-shaped structure is connected for use, the two prepared composite material box-shaped structures are symmetrically connected through a spanner by using a high-strength metal bolt, so that the connection of the aircrafts is realized.
The fiber reinforced composite aircraft cabin section connecting structure effectively increases the rigidity of the connecting structure through the combined action of the design of three box-shaped components and L-shaped components and the design that the thickness of a horizontal layer of the L-shaped components is 2 times of that of a vertical layer. The connecting structure is applied to an aircraft structure, effectively reduces stress concentration and ensures the aerodynamic appearance of the aircraft.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (6)
1. A fiber reinforced composite aircraft cabin section connecting structure is characterized by comprising two identical composite box-shaped structures and a high-strength metal bolt; the two composite material box-shaped structures are symmetrically connected from bottom to top through high-strength metal bolts;
each composite box-type structure comprises: a left box member, a middle box member, a right box member, and an L-shaped member; the L-shaped component comprises a horizontal plate and a vertical plate; and the thickness of the horizontal plate is 2 times of that of the vertical plate;
the left box-shaped component, the middle box-shaped component and the right box-shaped component are sequentially and uniformly distributed on the L-shaped component;
the left box-shaped component and the right box-shaped component are in a bilateral symmetry structure, and the left box-shaped component comprises a horizontal plate, a vertical plate and a right baffle; the right box-shaped component comprises a horizontal plate, a vertical plate and a left baffle; the middle box-shaped component comprises a horizontal plate, a vertical plate and a left baffle and a right baffle;
the horizontal plate widths of the three box-shaped members of the left box-shaped member, the middle box-shaped member and the right box-shaped member are all the same as the horizontal plate width of the L-shaped member; the vertical plates of the three box-shaped components have consistent sizes and are all smaller than the vertical plate of the L-shaped component;
the left side baffle of the middle box-shaped component is adjacently fixed with the right side baffle of the left box-shaped component, and the right side baffle of the middle box-shaped component is adjacently fixed with the left side baffle of the right box-shaped component; the four side baffles are completely the same, each side baffle is perpendicular to the L-shaped component horizontal plate, and the length of each side baffle is the same as the width of the L-shaped component horizontal plate;
a square opening which penetrates through the vertical plate of the L-shaped component at the same time is reserved on the central line of the vertical plate surface of the middle box-shaped component, the specific size of the square opening is selected according to the size of the actual aircraft, and four corners of the square opening are chamfers;
after the composite box-shaped structure is formed, a bolt hole is formed in the center line of the horizontal plate of the middle box-shaped component, and the bolt hole is located in the center line of the horizontal plate of the composite box-shaped structure.
2. A fiber-reinforced composite aircraft cabin connection according to claim 1, wherein the junction of the three box-shaped elements and the L-shaped element is a transitional junction.
3. A fiber-reinforced composite aircraft cabin segment connection structure according to claim 1, wherein said chamfer has a radius of 3 mm.
4. A fiber reinforced composite aircraft cabin connection structure according to claim 1, wherein the bolt holes are located at a distance 2/5 of the horizontal plate width from the centerline of the vertical plate of the composite box structure.
5. The method for preparing the fiber reinforced composite material aircraft cabin connecting structure according to claim 1, wherein the manufacturing process adopts a resin transfer molding forming process, and the specific manufacturing steps are as follows:
step one, respectively manufacturing a male die and a female die according to a composite material box-shaped structure;
aiming at two composite material box-shaped structures which are symmetrically connected from top to bottom through the bottom of the high-strength metal bolt, the whole composite material box-shaped structure is obtained by matching a male die and a female die;
step two, folding and molding the left box-shaped member, the middle box-shaped member, the right box-shaped member and the L-shaped member by using dry fibers;
in the folding process of the L-shaped component, the fiber laying mode of the horizontal plate is cross laying;
thirdly, coating toughened and reinforced resin on the left box-shaped member, the middle box-shaped member, the right box-shaped member and the L-shaped member which are formed by folding;
bonding the preformed left box-shaped component, the middle box-shaped component, the right box-shaped component and the L-shaped component according to a drawing, putting the bonded components into a male die and a female die for die assembly, injecting glue into the die through a glue injection hole, and finally curing at high temperature and high pressure to form a box-shaped structure;
step five, after the composite material box-shaped structure is manufactured, a bolt hole is formed in a horizontal plate of the composite material box-shaped structure;
and step six, when the composite material box-shaped structure is connected for use, the two prepared composite material box-shaped structures are symmetrically connected through a spanner by using a high-strength metal bolt, so that the connection of the aircrafts is realized.
6. The method according to claim 5, wherein in step one, square protrusions are left on the vertical plates of the middle box-shaped member and the L-shaped member of the male mold, and are used as cores for supporting square openings on the vertical plates of the middle box-shaped member; or square bulges are not left on the middle box-shaped component and the L-shaped component of the male die, and after the composite material box-shaped structure is manufactured, square openings are manually formed in the vertical plates on the middle box-shaped component and the L-shaped component.
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| CN201711014578.2A CN108032988B (en) | 2017-10-25 | 2017-10-25 | Fiber reinforced composite aircraft cabin connecting structure and preparation method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711014578.2A CN108032988B (en) | 2017-10-25 | 2017-10-25 | Fiber reinforced composite aircraft cabin connecting structure and preparation method thereof |
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| CN108032988A CN108032988A (en) | 2018-05-15 |
| CN108032988B true CN108032988B (en) | 2020-06-16 |
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| 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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| Publication number | Priority date | Publication date | Assignee | Title |
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| US8212194B2 (en) * | 2006-06-27 | 2012-07-03 | Hexcel Corporation | Aerospace articles made from quasi-isotropic chopped prepreg |
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2017
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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| CN108032988A (en) | 2018-05-15 |
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