CN206125443U - Dismantled and assembled compound material tail fairing - Google Patents
Dismantled and assembled compound material tail fairing Download PDFInfo
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- CN206125443U CN206125443U CN201621073803.0U CN201621073803U CN206125443U CN 206125443 U CN206125443 U CN 206125443U CN 201621073803 U CN201621073803 U CN 201621073803U CN 206125443 U CN206125443 U CN 206125443U
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- tail fairing
- assembly
- lid
- reinforcing ring
- fairing
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Abstract
The utility model discloses a dismantled and assembled compound material tail fairing, it includes that beaded finish, a plurality of longitudinal baffles, hoop strengthening rib, foams press from both sides core sub -assembly, inner skin, outer covering and a plurality of angle boxes, wherein, a plurality of longitudinal baffle settings between beaded finish and hoop strengthening rib, beaded finish, a plurality of longitudinal baffles all set up in inner skin with the hoop strengthening rib, and they form a plurality of mouth frame together, beaded finish, a plurality of longitudinal baffles, hoop strengthening rib, inner skin and outer coverings pass through carbon fabric tablet hot melt and form the carbon fabric shop layer pre -setting body, it is internal that carbon fabric shop layer pre -setting is arranged in to foam clamp core sub -assembly to it is fit to form tail fairing preforming body group through the hot melt, and tail fairing preforming body group zoarium and flap obtain the whole formed body of RTM through RTM forming technology together. The utility model discloses reduce part and mechanical connection, reduced the assembly degree of difficulty, improved appearance precision and surface quality.
Description
Technical field
The utility model belongs to field of airplane structure, is related to a kind of removable multiple material tail fairing.
Background technology
For ease of some military aircrafts（Such as fighter plane, attack plane and trainer aircraft）Engine stripping, install and safeguard,
Removable assembling structure is typically designed to positioned at the tail fairing of tail cone, is connected with fuselage end frame by quick-detachable lock or bolt.
At present the aircraft tail cover structure of home and abroad is metal structure, and most of is aluminium alloy thin-walled riveted structure,
There is number of parts many, riveting work amount is big；Inside and outside covering is thin, and malformation is larger；The shortcomings of structure is heavier.For removable
The tail fairing of dress, lid need to be opened up to provide installation path toward contact on tail fairing covering, need to be further added by a mouthful frame, section bar etc. zero
Part, number of parts, mechanical connection further increase, and assembly difficulty increase, weight accordingly increases.
Utility model content
The purpose of this utility model is both to have realized being detachably connected with body, and metal current thin-wall construction machine is solved again
The poor rigidity that hood is present, malformation is big, number of parts is more, and riveting work amount is big and the problems such as heavier structure, so as to provide
A kind of removable multiple material tail fairing.
In order to realize the purpose of this utility model, the technical solution adopted in the utility model is：
A kind of removable multiple material tail fairing, it includes reinforcing ring, some pieces of longitudinal baffles, modal circumferential stiffening rib, foam folders
Core assembly, inside panel, exterior skin and several angle boxes, wherein, some pieces of longitudinal baffles are arranged on reinforcing ring and strengthen with ring
Between muscle, the reinforcing ring, some pieces of longitudinal baffles and modal circumferential stiffening rib are arranged at Inner Mongol intracutaneous, and they form together some
Individual mouth frame, the reinforcing ring, some pieces of longitudinal baffles, modal circumferential stiffening rib, inside panel and exterior skins pass through carbon fibre fabric tablet
Hot melt forms carbon fibre fabric laying pre-setting body；Foam core sub-assembly is placed in carbon fibre fabric laying pre-setting body, and
Tail fairing preform assembly is formed by hot melt, tail fairing preform assembly and lid are molded work by RTM together
Skill obtains RTM global formation bodies, is connected needs with body further according to tail fairing and several are arranged on longitudinal baffle for fuselage end
The angle box of frame connection.
Further, the foam core sub-assembly is placed between inside panel and exterior skin.
Further, lid is connected by screw and plate nut with tail fairing RTM global formation bodies.
Further, lid is composite material element, and the surrounding of lid is uniform with exterior skin gap clearance.
Further, the angle box is trapezoidal rod structure, and stile is riveted and centre is provided with positioning on the inside of angle cassette bottom and reinforcing ring
Hole；One side of trapezoidal column rivets with the interlayer of interior exterior skin, and another side rivets with the stile of longitudinal baffle.
The utility model can not only meet the dismounting of tail fairing and use function, and can mitigate tail fairing weight, reduce
Number of parts and mechanical connection, reduce assembly difficulty, and can control structure deformation, raising form accuracy and surface quality.
Description of the drawings
Fig. 1 is mounting structure schematic diagram of the present utility model
Fig. 2 is the sectional view of A-A in Fig. 1
Fig. 3 is the A of Fig. 1 to partial view
Fig. 4 is the B-B sectional views of Fig. 3
Fig. 5 is structural representation of the present utility model
Fig. 6 is the C-C sectional views of Fig. 5
In figure；Tail fairing 1, lid 2, angle box 3, bolt 4, guide finger 5, fuselage end frame 6, longitudinal baffle 11, reinforcing ring
101, modal circumferential stiffening rib 102, inside panel 103, foam core sub-assembly 104, exterior skin 105.
Specific embodiment
The utility model is further illustrated with reference to the accompanying drawings and examples：
Embodiment 1：As shown in figures 1 to 6, a kind of removable multiple material tail fairing, it includes reinforcing ring 101, some pieces of longitudinal directions
Dividing plate 11, modal circumferential stiffening rib 102, foam core sub-assembly 104, inside panel 103, exterior skin 105 and several angle boxes 3, wherein,
Some pieces of longitudinal baffles 11 are arranged between reinforcing ring 101 and modal circumferential stiffening rib 102, the reinforcing ring 101, some pieces of longitudinal directions every
Plate 11 is arranged in inside panel 103 with modal circumferential stiffening rib 102, and they form together each lid on several mouthful of frame reinforcement covering
The structural strength and rigidity of structural strength and raising tail fairing at 2 openings.The reinforcing ring 101, some pieces of longitudinal baffles 11, ring
Heated by carbon fibre fabric tablet to reinforcement 102, inside panel 103 and exterior skin 105 to be formed carbon fibre fabric laying make a reservation for
Type body；Foam core sub-assembly 104 is placed in carbon fibre fabric laying pre-setting body, and it is preforming to form tail fairing by hot melt
Body assembly, after preform assembly correct position is outputed respectively and posts the lid of demoulding cloth, tail fairing preform
Assembly and lid obtain RTM global formations body and lid by RTM moulding process together, are connected with body further according to tail fairing
Needs arrange several on longitudinal baffle and rivet for the angle box 3 of fuselage end frame connection and with RTM global formations body, final to obtain
A kind of removable multiple material tail fairing.
Wherein exterior skin 105 is determined by Aerodynamic Configuration of Aireraft；Inside panel 103 is needed by the injection air-flow rectification in enging cabin
Determine；Foam core sub-assembly 104 is placed between inside panel 103 and exterior skin 105, and the cavity formed by interior exterior skin is true
It is fixed, can add to form pre-setting body using machine；Reinforcing ring 101, modal circumferential stiffening rib 102, longitudinal baffle 11 are a kind of form of section bar,
The concrete form of section bar can be according to actual needs selected, and makes they and interior exterior skin global formation, not only increase tail fairing
The intensity and rigidity of structure, and lid opening is able to reinforcement, reaches the effect of one-object-many-purposes.
The lid by dismounting, safeguard it needs to be determined that, each lid is by some screws and plate nut and tail fairing RTM
Global formation body connects.
Wherein lid 2 is composite material element, is made together with RTM global formation bodies, not only can save a set of lid mould
The manufacturing expense of tool, and the existing good profile of lid 2 is can ensure that, and between inside panel 103, the opposite joint of exterior skin 105
Gap is uniform.
The angle box 3 is trapezoidal rod structure, and stile is riveted and centre is provided with location hole on the inside of angle cassette bottom and reinforcing ring；It is trapezoidal
One side of post rivets with the interlayer of interior exterior skin, and another side rivets with the stile of longitudinal baffle.
Embodiment 2：As Figure 1-4,
During installation, bolt 4, guide finger 5 are separately fixed on fuselage end frame 6, tail fairing 1 is by being fixed on fuselage end frame 6
On the centering tail fairing 1 of guide finger 5 on reinforcing ring 101 and angle box 3 on location hole, be fixed on end frame 6 on bolt 4 distinguish
Through after the bolt hole on the reinforcing ring 101 and angle box 3 on tail fairing, by the mounting gasket of lid 2, nut and insure, by machine
Hood load reaches fuselage end frame.Lid is connected again by screw-plate nut with RTM global formation bodies, is opened up on covering
Lid provides installation path or safeguards needs for bolt.
When dismounting and safeguarding engine, can pass through first to pull down each lid screw and the lid 2 on tail fairing respectively, then open
Nuts and washers is pulled down after each bolt-lock, is pulled back and is pulled down tail fairing.
Processing method of the present utility model is summarized as follows,
The first step, designs a set of tail fairing monoblock type gel-injection mould；
Second step, the carbon fibre fabric tablet made is laid successively by design ply stacking-sequence in internal model, and is divided
The carbon fibre fabric laying pre-setting of reinforcing ring 101, longitudinal baffle 11, modal circumferential stiffening rib 102, inside panel 103 Re Rong not formed
Body；
3rd step, by light closed hole rigid foaming material foam core sub-assembly 104 is machined into；
4th step, the foam core sub-assembly 104 in the 3rd step is placed in the carbon fibre fabric laying obtained in second step
In pre-setting body, then lay successively the carbon fibre fabric tablet of exterior skin 105 made and hot melt form tail fairing pre-setting body
Assembly；
5th step, after preform assembly correct position is outputed respectively and cuts lid 2, in the inner surface of lid 2
One layer of demoulding cloth of patch, makes lid 2 isolate when RTM is molded together with longitudinal baffle 11, modal circumferential stiffening rib 101 and reinforcing ring 102；
6th step, the tail fairing pre-setting body assembly obtained in the 5th step is put in gel-injection mould, covers injecting glue mould
The external mold of tool, is foamed after matched moulds, resin injection, is obtained RTM after solidification and the composite RTM moulding process operations such as the demoulding
Global formation body and lid 2；
7th step, machining is prepared after each angle box 3, completes the riveting of each angle box 3 and RTM global formation bodies, and at angle
Coordinate together to output each guide through hole and bolt hole on box 3 and reinforcing ring 101；
8th step, completes the connection of each lid 2 and RTM global formation bodies, finally obtains this product.
Claims (5)
1. one kind is removable answers material tail fairing, it is characterised in that it includes that reinforcing ring, some pieces of longitudinal baffles, rings are strengthened
Muscle, foam core sub-assembly, inside panel, exterior skin and several angle boxes, wherein, some pieces of longitudinal baffles be arranged on reinforcing ring with
Between modal circumferential stiffening rib, the reinforcing ring, some pieces of longitudinal baffles and modal circumferential stiffening rib are arranged at Inner Mongol intracutaneous, and they are together
Several mouthful of frame is formed, the reinforcing ring, some pieces of longitudinal baffles, modal circumferential stiffening rib, inside panel and exterior skins pass through carbon fiber
Fabric web heats to form carbon fibre fabric laying pre-setting body；Foam core sub-assembly is placed in carbon fibre fabric laying pre-setting
In vivo, and by hot melt tail fairing preform assembly is formed, tail fairing preform assembly and lid pass through together RTM
Moulding process obtains RTM global formation bodies, is connected needs with body further according to tail fairing and several confessions are arranged on longitudinal baffle
The angle box of fuselage end frame connection.
2. one kind according to claim 1 is removable answers material tail fairing, it is characterised in that the foam core sub-assembly
It is placed between inside panel and exterior skin.
3. one kind according to claim 2 is removable answers material tail fairing, it is characterised in that lid is by screw and supporting plate
Nut is connected with tail fairing RTM global formation bodies.
4. one kind according to claim 3 is removable answers material tail fairing, it is characterised in that lid is composite material element,
The surrounding of lid is uniform with exterior skin gap clearance.
5. one kind according to claim 2 is removable answers material tail fairing, it is characterised in that the angle box is trapezoidal column knot
Stile is riveted and centre is provided with location hole on the inside of structure, angle cassette bottom and reinforcing ring；The interlayer riveting of one side of trapezoidal column and interior exterior skin
Connect, another side rivets with the stile of longitudinal baffle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621073803.0U CN206125443U (en) | 2016-09-23 | 2016-09-23 | Dismantled and assembled compound material tail fairing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621073803.0U CN206125443U (en) | 2016-09-23 | 2016-09-23 | Dismantled and assembled compound material tail fairing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206125443U true CN206125443U (en) | 2017-04-26 |
Family
ID=58570341
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621073803.0U Active CN206125443U (en) | 2016-09-23 | 2016-09-23 | Dismantled and assembled compound material tail fairing |
Country Status (1)
| Country | Link |
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| CN (1) | CN206125443U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106347684A (en) * | 2016-09-23 | 2017-01-25 | 江西洪都航空工业集团有限责任公司 | Detachable composite tail fairing and machining method thereof |
| CN107856878A (en) * | 2017-11-01 | 2018-03-30 | 北京星航机电装备有限公司 | A kind of small thickness high-temperature-resistant structure assembly and disassembly methods of large scale |
| CN108820246A (en) * | 2018-07-25 | 2018-11-16 | 中国科学院工程热物理研究所 | A kind of small-size turbojet engine quickly upper machine mounting structure and method |
| CN109747181A (en) * | 2019-03-04 | 2019-05-14 | 保定国奥新能源工程材料科技有限责任公司 | The manufacturing method of duct |
| CN114434835A (en) * | 2022-01-25 | 2022-05-06 | 南京晨光集团有限责任公司 | Forming tool and forming method for long-cone composite structural member of aircraft |
-
2016
- 2016-09-23 CN CN201621073803.0U patent/CN206125443U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106347684A (en) * | 2016-09-23 | 2017-01-25 | 江西洪都航空工业集团有限责任公司 | Detachable composite tail fairing and machining method thereof |
| CN107856878A (en) * | 2017-11-01 | 2018-03-30 | 北京星航机电装备有限公司 | A kind of small thickness high-temperature-resistant structure assembly and disassembly methods of large scale |
| CN108820246A (en) * | 2018-07-25 | 2018-11-16 | 中国科学院工程热物理研究所 | A kind of small-size turbojet engine quickly upper machine mounting structure and method |
| CN109747181A (en) * | 2019-03-04 | 2019-05-14 | 保定国奥新能源工程材料科技有限责任公司 | The manufacturing method of duct |
| CN114434835A (en) * | 2022-01-25 | 2022-05-06 | 南京晨光集团有限责任公司 | Forming tool and forming method for long-cone composite structural member of aircraft |
| CN114434835B (en) * | 2022-01-25 | 2024-01-05 | 南京晨光集团有限责任公司 | Forming tool and forming method for long-cone composite structural member of aircraft |
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