CN104724277B - Light aerocraft composite thin skin entirety fast joint structure and preparation method thereof - Google Patents
Light aerocraft composite thin skin entirety fast joint structure and preparation method thereof Download PDFInfo
- Publication number
- CN104724277B CN104724277B CN201510053729.XA CN201510053729A CN104724277B CN 104724277 B CN104724277 B CN 104724277B CN 201510053729 A CN201510053729 A CN 201510053729A CN 104724277 B CN104724277 B CN 104724277B
- Authority
- CN
- China
- Prior art keywords
- thin skin
- composite thin
- cingulum
- mushroom head
- composite
- 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.)
- Active
Links
Abstract
The invention discloses a kind of light aerocraft composite thin skin entirety fast joint structure, quickly connected by industrial cingulum between the aircraft truss and composite thin skin, the industrial cingulum uses mushroom head cingulum, and the mushroom head cingulum includes engaged the first mushroom head and the second mushroom head；Preparation method：Part needed for selection；Pair determine part cleared up and handled；The second mushroom head is bonded on composite thin skin first, then fitted in the first mushroom head on aircraft truss, finally by composite thin skin parallel laid on aircraft truss structure；Complete the fixation of composite thin skin.By the above-mentioned means, the present invention can ensure material integrity, avoid because machinery or stress cause crackle so as to improve composite thin skin service life；Composite thin skin Fast Installation, positioning can be improved efficiency of assembling during installation；Easy to disassemble, industrial cingulum can repeat folding more than hundreds of times.
Description
Technical field
The present invention relates to technical field of aerospace, integrally quickly connects more particularly to a kind of light aerocraft composite thin skin
Binding structure and preparation method thereof.
Background technology
Composite can significantly be dropped with the features such as its thermal coefficient of expansion is small, antifatigue and vibration resistance is strong, anticorrosive
Low part, fastener quantity improve integrally-built combination property, turn into four big main material of aircraft body structure of new generation it
One.Compared with metal structure, the weakness such as composite interlayer low intensity, impact resistance difference, determine that the assembling of its structure connects
Connect that difficulty is big, technical requirements are high.
The type of attachment and method of composite rationally and are neatly used, is to improve composite material structural member intensity, subtract
One of light construction weight, the essential condition for giving full play to composite excellent specific property.Between composite material parts or composite
Assembly connection between metal parts, generally there are 3 kinds of mechanical connection, splicing and Hybrid connections methods.Connected in composite
In technology, from which kind of connection method, mainly depending on actual operation requirements.In general, when carry it is larger,
When reliability requirement is higher, mechanical connection is preferably used；When carrying is smaller, component is relatively thin, environmental condition is not very severe, preferably adopt
Connected with being glued；It is some in particular cases, for improve structure fail safety characteristic when, Hybrid connections can be used.
The anisotropy of composite thin plate, the features such as breaking strain is small make it that composite connection is increasingly complex, compound
Material is more difficult when processing hole, and the distribution of cut staple around-the-hole stress is complex, and stress concentration degree height, which easily produces, to be split
Line causes its intensity degradation, therefore is the weak link of structure in composite connection, is badly in need of research one kind and does not damage material
The attachment structure that material structure and can is accurately positioned, assembled, it can effectively solve the problem that light aerocraft composite thin skin produces because of riveting
The problems such as raw internal stress generation material crack and rapid disassembling are safeguarded.
The content of the invention
The present invention solves the technical problem of provide one kind to can effectively solve the problem that composite thin skin because of machinery even
Connect caused material crack and facilitate demolition and maintenance, the light aerocraft composite thin skin for improving efficiency of assembling problem is integrally fast
Fast attachment structure and preparation method thereof.
In order to solve the above technical problems, one aspect of the present invention is：A kind of light aerocraft composite wood is provided
Expect thin skin entirety fast joint structure, including, aircraft truss and composite thin skin, the aircraft truss and composite
Quickly connected by industrial cingulum between thin skin, the industrial cingulum uses mushroom head cingulum, and the mushroom head cingulum includes
Engaged the first mushroom head and the second mushroom head, and the back side of the first mushroom head and the second mushroom head is equipped with glue-line, the
One mushroom head is fixed on aircraft truss by glue-line, and second mushroom head is fixed on composite thin skin by glue-line
On.
In a preferred embodiment of the present invention, T-slot is provided with the middle part of the aircraft truss, the T-slot both sides are peace
Fill the locating surface of composite thin skin.
In a preferred embodiment of the present invention, the composite thin skin is fast with aircraft truss on the basis of locating surface
Speed connection.
In a preferred embodiment of the present invention, the aluminium alloy of fixing composite material thin skin is installed in the T-slot
Pressing plate.
In a preferred embodiment of the present invention, the peel strength of the mushroom head cingulum is less than or equal to 6N ~ 7N, mushroom head
Cingulum width 23cm-28cm.
In order to solve the above technical problems, another technical solution used in the present invention is：It is compound to provide a kind of light aerocraft
The preparation method of material thin skin entirety fast joint structure, comprises the following steps：
Step 1：Industrial cingulum is chosen, the peel strength being stripped when being fastened by industrial cingulum determines that composite is thin
Heating-up temperature and heating side when the sectional dimension of covering, the thickness of composite thin skin, industrial cingulum glue-line bond for the first time
Formula；
Step 2：The part determined to step 1 is cleared up and handled；
Step 3：Complete the laying of composite thin skin, the bonding of industrial cingulum；
The glue-line of the second mushroom head in mushroom head cingulum is bonded to the thin illiteracy of composite by way of heating first
Pi Shang, then the first mushroom head glue-line is fitted in by way of heating on aircraft truss, finally by composite thin skin
Parallel laid is on aircraft truss structure；
Step 4：Complete the fixation of composite thin skin；
Aircraft truss structure will be assemblied in for the aluminium alloy pressing plate for compressing composite thin skin, passes through sunk screw
It is fixed on aircraft truss structure；
Step 5：After said structure installation, integral composite light-skinned structure debugging is carried out.
The sectional dimension of composite thin skin is 900mm ~ 1100mm × 400 ~ 600mm, the thickness of composite thin skin
Spend 0.5mm ~ 1mm.
In a preferred embodiment of the present invention, mode of heating when industrial cingulum glue-line bonds for the first time adds for heating rod
Heat.
The beneficial effects of the invention are as follows：
（1）Composite thin skin need to not use machine drilling, be bonded using industrial cingulum glue-line, ensure that material is complete
Property, avoid because machinery or stress cause crackle so as to improve composite thin skin service life.
（2）Using the surface of industrial hasp mushroom head moulding it is engaged when can meet its bonding strength requirement, during installation
Composite thin skin Fast Installation, positioning can be improved efficiency of assembling.
（3）In light aerocraft maintenance maintenance, composite thin skin is easy to disassemble, and industrial cingulum can repeat folding number
More than hundred times.
（4）Using industrial cingulum either in resetting still in the function such as structure-reinforced, glue is in stress distribution
It is more average, the single point pressure being mechanically fixed can be excluded, while the material telescopic shape change brought by the temperature difference can be buffered, in dynamic
And stable adhesion is all kept under static state between different structure.
Brief description of the drawings
Technical scheme in order to illustrate the embodiments of the present invention more clearly, make required in being described below to embodiment
Accompanying drawing is briefly described, it should be apparent that, drawings in the following description are only some embodiments of the present invention, for
For those of ordinary skill in the art, on the premise of not paying creative work, it can also be obtained according to these accompanying drawings other
Accompanying drawing, wherein：
Fig. 1 is the one preferable of mushroom head cingulum in light aerocraft composite thin skin entirety fast joint structure of the present invention
The structural representation of embodiment；
Fig. 2 is a preferable reality of aircraft truss in light aerocraft composite thin skin entirety fast joint structure of the present invention
Apply the structural representation of example；
Fig. 3 is one of composite thin skin in light aerocraft composite thin skin entirety fast joint structure of the present invention
The structural representation of preferred embodiment；
Fig. 4 is to be used for composite thin skin in light aerocraft composite thin skin entirety fast joint structure of the present invention
The structural representation of one preferred embodiment of the aircraft truss of positioning；
Fig. 5 is the preferable reality after the completion of light aerocraft composite thin skin entirety fast joint structure assembling of the present invention
Apply the structural representation of example；
The mark of each part is as follows in accompanying drawing：101- glue-lines, the mushroom heads of 102- first, 103- release liners, the mushrooms of 104- second
Mushroom head, 201- aircraft truss, 202- composite thin skins, 401-T type grooves, 402- locating surfaces, 501- aluminium alloy pressing plates.
Embodiment
The technical scheme in the embodiment of the present invention will be clearly and completely described below, it is clear that described implementation
Example is only the part of the embodiment of the present invention, rather than whole embodiments.It is common based on the embodiment in the present invention, this area
All other embodiment that technical staff is obtained under the premise of creative work is not made, belong to the model that the present invention protects
Enclose.
The embodiment of the present invention includes：
A kind of light aerocraft composite thin skin entirety fast joint structure, including, aircraft truss 201 and composite
Thin skin 202, quickly connected by industrial cingulum between the aircraft truss 201 and composite thin skin 202.
Due to hole machined can not be carried out to composite thin skin 202, in order to ensure its bulk strength, pass through applicable industry
Cingulum can improve the stressing conditions of composite thin skin 202, while be easy to dismounting to safeguard, so as to expand its application field, carry
Its high application.
The industrial cingulum is mono- using T300 using the mushroom head cingulum for having sufficiently high peel strength, composite material skin
Xiang Bu, laying 90/45/0/-45/-90, is integrally formed through autoclave.
As shown in figure 1, the mushroom head cingulum includes engaged the first mushroom head 102 and the second mushroom head 104, and
The back side of first mushroom head 102 and the second mushroom head 104 is equipped with glue-line 101, and glue-line 101 has release above before being not used
Paper 103, release liners 103 are opened during use.Glue-line 101 can be applied into certain pressure by way of heating to paste it into
On composite thin skin 202 and aircraft truss 201, it can keep stablizing adhesion between industrial cingulum and part in the absence of single
Point is by force phenomenon.
The present invention's is preferable to carry out, and the first mushroom head 102 is fixed on aircraft truss 201 by glue-line 101, and described the
Two mushroom heads 104 are fixed on composite thin skin 202 by glue-line 101, as shown in Figures 2 and 3.
Affiliated aircraft truss 201 meets light-weight design, ensures sufficient intensity requirement, and it is fixed to be designed with junction
Plane 402 and required mounting and positioning device, ensure that connection can Fast Installation positioning.
Therefore, as shown in figure 4, the middle part of the aircraft truss 201 is provided with T-slot 401, the both sides of T-slot 401 are installation
The locating surface 402 of composite thin skin 202.The composite thin skin 202 on the basis of locating surface 402 with aircraft truss
201 quick connections.The effect of locating surface 402 is can quickly and accurately to determine the installation site of composite thin skin 202.
The aluminium alloy pressing plate 501 of fixing composite material thin skin 202 is installed in the T-slot 401, and uses sunk screw
It is fixed in the structure of aircraft truss 201.As shown in figure 5, this structure can resist light aerocraft caused vibrations etc. awing
Situation, while installation strength requirement can be ensured.
In addition, the preparation method of 202 overall fast joint structure of light aerocraft composite thin skin, including following step
Suddenly：
Step 1：According to the different application scope of magic tape, industrial cingulum is chosen, is stripped when being fastened by industrial cingulum
Peel strength determine the sectional dimension of composite thin skin 202, the thickness of composite thin skin 202, industrial cingulum glue
Heating-up temperature and mode of heating when layer 101 bonds for the first time；
Step 2：The part determined to step 1 is cleared up and handled；Including the section hair of composite thin skin 202
Thorn and the cleaning of the supporting surface of aircraft truss 201, composite thin skin 202 and the supporting surface of aircraft truss 201 should be cleaned, dried；
Step 3：Complete the laying of composite thin skin 202, the bonding of industrial cingulum；
The glue-line 101 of the second mushroom head 104 in mushroom head cingulum is bonded to composite wood by way of heating first
Expect on thin skin 202, then fit in the glue-line 101 of the first mushroom head 102 on aircraft truss 201 by way of heating, most
Afterwards by the parallel laid of composite thin skin 202 in the structure of aircraft truss 201；
Step 4：Complete the fixation of composite thin skin 202；
The structure of aircraft truss 201 will be assemblied in for compressing the aluminium alloy pressing plate 501 of composite thin skin 202, led to
Sunk screw is crossed to be fixed in the structure of aircraft truss 201；
Step 5：After said structure installation, the structural adjustment of integral composite thin skin 202 is carried out.
Wherein, mode of heating when the preferred industrial cingulum glue-line 101 of the present invention bonds for the first time is that heating rod heats.By adding
Hot pin heating glue-line 101 pastes industrial cingulum on aircraft truss 201 and composite thin skin 202.
The preferred embodiments of the present invention 1：Based on above-mentioned fast joint structure, wherein, the stripping of the mushroom head cingulum is strong
Degree is less than or equal to 6N, mushroom head cingulum width 23cm.
The sectional dimension of composite thin skin 202 is 900mm × 400, the thickness 0.8mm of composite thin skin 202.
The present invention's is preferable to carry out 2：Based on above-mentioned fast joint structure, the maximum peeling strength of the mushroom head cingulum is small
In equal to 6.66N, mushroom head cingulum width 25cm.
The sectional dimension of composite thin skin 202 is 1000mm × 500mm, the thickness of composite thin skin 202
0.5mm。
The present invention's is preferable to carry out 3：Based on above-mentioned fast joint structure, the peel strength of the mushroom head cingulum is less than etc.
In 7N, mushroom head cingulum width 28cm.
The sectional dimension of composite thin skin 202 is 1100mm × 600mm, the thickness of composite thin skin 202
1mm。
The present invention includes advantages below：
Composite thin skin 202 need to not use machine drilling, be bonded using industrial cingulum glue-line 101, ensure that material is complete
Whole property, avoid because machinery or stress cause crackle so as to improve the service life of composite thin skin 202.
Using the surface of industrial hasp mushroom head moulding it is engaged when can meet its bonding strength requirement, can be with during installation
The Fast Installation of composite thin skin 202, positioning are improved into efficiency of assembling.
In light aerocraft maintenance maintenance, composite thin skin 202 is easy to disassemble, and industrial cingulum can repeat folding number
More than hundred times.
Using industrial cingulum either in resetting still in the function such as structure-reinforced, glue in stress distribution more
It is average, the single point pressure being mechanically fixed can be excluded, while the material telescopic shape change brought by the temperature difference can be buffered, dynamically and quiet
Stable adhesion is all kept under state between different structure.
Embodiments of the invention are the foregoing is only, are not intended to limit the scope of the invention, it is every to utilize this hair
The equivalent structure or equivalent flow conversion that bright description is made, or directly or indirectly it is used in other related technology necks
Domain, it is included within the scope of the present invention.
Claims (3)
1. a kind of light aerocraft composite thin skin entirety fast joint structure, including, aircraft truss and the thin illiteracy of composite
Skin, quickly connected by industrial cingulum between the aircraft truss and composite thin skin, it is characterised in that the industry button
Band uses mushroom head cingulum, and the mushroom head cingulum includes engaged the first mushroom head and the second mushroom head, and the first mushroom
The back side of mushroom head and the second mushroom head is equipped with glue-line, and the first mushroom head is fixed on aircraft truss by glue-line, and described second
Mushroom head is fixed on composite thin skin by glue-line；Light aerocraft composite thin skin entirety fast joint structure
Preparation method, it is characterised in that comprise the following steps：
Step 1：Industrial cingulum is chosen, the peel strength being stripped when being fastened by industrial cingulum determines composite thin skin
Heating-up temperature and mode of heating when bonding for the first time of sectional dimension, the thickness of composite thin skin, industrial cingulum glue-line；
Step 2：The part determined to step 1 is cleared up and handled；
Step 3：Complete the laying of composite thin skin, the bonding of industrial cingulum；
The glue-line of the second mushroom head in mushroom head cingulum is bonded to by way of heating on composite thin skin first,
Then the first mushroom head glue-line is fitted in by way of heating on aircraft truss, finally by composite thin skin parallel laid
It is located on aircraft truss structure；
Step 4：Complete the fixation of composite thin skin；
Aircraft truss structure will be assemblied in for the aluminium alloy pressing plate for compressing composite thin skin, be fixed by sunk screw
In on aircraft truss structure；
Step 5：After said structure installation, integral composite light-skinned structure debugging is carried out；
T-slot is provided with the middle part of the aircraft truss, the T-slot both sides are the locating surface of installation composite thin skin；It is described
Composite thin skin is quickly connected on the basis of locating surface with aircraft truss；Fixing composite material is installed in the T-slot
The aluminium alloy pressing plate of thin skin；
Composite material skin uses unidirectional cloth, laying 90/45/0/-45/-90, is integrally formed through autoclave, composite is thin
The sectional dimension of covering is 900mm ~ 1100mm × 400 ~ 600mm, thickness 0.5mm ~ 1mm of composite thin skin.
2. light aerocraft composite thin skin entirety fast joint structure according to claim 1, it is characterised in that institute
The peel strength for stating mushroom head cingulum is less than or equal to 6N ~ 7N, mushroom head cingulum width 23cm-28cm.
3. light aerocraft composite thin skin entirety fast joint structure according to claim 1, it is characterised in that work
Mode of heating when industry cingulum glue-line bonds for the first time heats for heating rod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510053729.XA CN104724277B (en) | 2015-02-03 | 2015-02-03 | Light aerocraft composite thin skin entirety fast joint structure and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510053729.XA CN104724277B (en) | 2015-02-03 | 2015-02-03 | Light aerocraft composite thin skin entirety fast joint structure and preparation method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104724277A CN104724277A (en) | 2015-06-24 |
| CN104724277B true CN104724277B (en) | 2017-11-24 |
Family
ID=53448818
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510053729.XA Active CN104724277B (en) | 2015-02-03 | 2015-02-03 | Light aerocraft composite thin skin entirety fast joint structure and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104724277B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU209465U1 (en) * | 2021-09-28 | 2022-03-16 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Composite vehicle compartment shell |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106114915B (en) * | 2016-08-26 | 2018-08-31 | 西安融智航空科技有限公司 | A kind of safeguard structure of interconnected carrying heat-insulation integrative |
| CN106394860B (en) * | 2016-11-25 | 2018-11-09 | 中国工程物理研究院总体工程研究所 | Disengageable skin connecting structure after stress |
| CN106997987A (en) * | 2017-05-19 | 2017-08-01 | 哈尔滨哈玻拓普复合材料有限公司 | Metal frames radome triangular element block and its manufacture method |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4813202A (en) * | 1987-05-22 | 1989-03-21 | Grumman Aerospace Corporation | Structural members connected by interdigitating portions |
| US4909659A (en) * | 1989-02-06 | 1990-03-20 | Grumman Aerospace Corporation | Interlocking structural members employing transverse locking means |
| DE102007054053A1 (en) * | 2007-11-13 | 2009-05-20 | Airbus Deutschland Gmbh | Coupling element for connecting two longitudinal stiffening elements |
| CN201559596U (en) * | 2009-11-20 | 2010-08-25 | 北汽福田汽车股份有限公司 | Connecting structure of automobile interior-decoration guard plate |
| CN202140385U (en) * | 2011-07-25 | 2012-02-08 | 重庆嘉皇汽车配件有限公司 | Snap button with dual lock |
| EP2730495B1 (en) * | 2012-11-13 | 2016-04-27 | Airbus Operations GmbH | Shell structure of a fuselage |
-
2015
- 2015-02-03 CN CN201510053729.XA patent/CN104724277B/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU209465U1 (en) * | 2021-09-28 | 2022-03-16 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Composite vehicle compartment shell |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104724277A (en) | 2015-06-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104724277B (en) | Light aerocraft composite thin skin entirety fast joint structure and preparation method thereof | |
| JP5731192B2 (en) | COMPOSITE STRUCTURE COMPRISING STRINGER HAVING PAD EMBEDDED IN PANEL CONCRETE AND METHOD OF TRANSMITTING FORCE | |
| KR101859783B1 (en) | Composite structures having composite-to-metal joints and method for making the same | |
| CN103661918B (en) | The composite airplane wings of bonding | |
| Yoo et al. | Parametric study on static and fatigue strength recovery of scarf-patch-repaired composite laminates | |
| JP6119044B2 (en) | Composite beam chord material between reinforcing plates and associated manufacturing method | |
| JP6074247B2 (en) | Method and apparatus for making large scale integrated airfoil | |
| US4793727A (en) | Two-step composite joint | |
| Khalili et al. | Numerical analysis of adhesively bonded T-joints with structural sandwiches and study of design parameters | |
| EP2551094B1 (en) | Bond and stitch repair for delaminated composite | |
| JP6758892B2 (en) | Thea strap embedded in a metal structure | |
| CN105501428A (en) | Composite structure having composite-to-metal joints and method for making same | |
| JP2014500185A5 (en) | ||
| US20160076387A1 (en) | Tooling for fastening metal reinforcement on the leading edge of a turbine engine blade, and a method using such tooling | |
| KR20110065526A (en) | Joint between aircraft components | |
| CN104787301B (en) | A kind of ultralight aircraft skin fast joint structure of segmented and preparation method | |
| ATE332269T1 (en) | METHOD FOR PRODUCING AND INDIRECTLY TESTING A COMPOSITE LAYER ON A MISSILE COMPONENT | |
| US9505491B2 (en) | Helicopter composite blade spar and method | |
| CN102424107A (en) | Manufacture method of solar airplane | |
| DK177650B1 (en) | Bond line assembly, method of joining composite parts, and use thereof | |
| CN105172317A (en) | Solidified composite and enhancing method of repairing structure and connecting structure of solidified composite | |
| JP5628313B2 (en) | Laminated composite rod, its manufacturing method and use in composite structure | |
| Srinivasan et al. | Comparative study of composite scarf and strap joints for equivalent repair signature under uniaxial tension | |
| CN202267649U (en) | Curved surface stripping clamp and curved surface bond quality testing system for weaved gasket of oscillating bearing | |
| US20140363294A1 (en) | Thermographic Inspection System for Composite Wind Turbine Blade |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20190221 Address after: 213000 No. 199 Fenglin South Road, Wujin High-tech Industrial Development Zone, Changzhou City, Jiangsu Province Co-patentee after: Xinyu Defense Technology Co., Ltd. Patentee after: New United Group Co., Ltd. Address before: 213164 Fenglin Road 68, hi tech Industrial Development Zone, Wujin District, Changzhou, Jiangsu Patentee before: New United Group Co., Ltd. |