CN206598973U - A kind of helicopter composite material girder construction - Google Patents
A kind of helicopter composite material girder construction Download PDFInfo
- Publication number
- CN206598973U CN206598973U CN201621303414.2U CN201621303414U CN206598973U CN 206598973 U CN206598973 U CN 206598973U CN 201621303414 U CN201621303414 U CN 201621303414U CN 206598973 U CN206598973 U CN 206598973U
- Authority
- CN
- China
- Prior art keywords
- composite material
- girder construction
- helicopter
- layer
- helicopter 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
Classifications
-
- 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
Landscapes
- Bridges Or Land Bridges (AREA)
Abstract
The utility model provides a kind of helicopter composite material girder construction, is related to helicopter structure design field.Including buried layer and clad, by the first skeleton (1) back to setting and buried layer of the second skeleton (2) as the helicopter composite material girder construction, first skeleton (1) is with the second skeleton (2) in upper and lower ends mutually back to bending, edge strip joint face and lower edge strip joint face in formation, by the upper laying layer (3) for coating the upper edge strip joint face, the lower laying layer (4) of the lower edge strip joint face and the left web laying layer (5) and right web laying layer (6) in the cladding buried layer centre position are coated as the clad of the helicopter composite material girder construction.The utility model uses RTM technological formings, by Varying-thickness web, and directly, web is difficult unstable failure to load path, and process implementing is easy, compared with traditional aluminium alloy girder construction, and loss of weight is up to 20%.
Description
Technical field
The utility model is related to helicopter structure design field, and in particular to a kind of helicopter composite material girder construction.
Background technology
Beam is one of main force support structure of helicopter, carries what is transmitted during each flight attitude of helicopter and landing
Load.Traditional helicopter girder construction is typically added by aluminum alloy materials machine to be formed, and density is larger, is unfavorable for structure loss of weight.Therewith
Compare, composite has the advantages that specific strength is high, specific modulus is big, designability is strong, is straight using the material substitution aluminium alloy
The important development trend of the machine of liter loss of weight design.Existing Composites Molding Techniques are limited by Forming Quality and cost, product
It is less to apply in main force support structure, hinder large-scale application of the composite structure on helicopter.
Utility model content
The purpose of this utility model is to provide a kind of helicopter composite material girder construction design side of use RTM technological formings
Case, is difficult on Helicopter Main load-carrying construction realize the problem of applying to solve conventional composite materials forming technique.
The utility model helicopter composite material girder construction, mainly includes buried layer and clad, by back to the of setting
One skeleton and the second skeleton are as the buried layer of the helicopter composite material girder construction, and the first skeleton and the second skeleton are upper
Lower two ends are mutually back to bending, edge strip joint face and lower edge strip joint face in is formationed, by the upper of the cladding upper edge strip joint face
Lay the left web laying layer of layer, the lower laying layer of the cladding lower edge strip joint face and the cladding buried layer centre position
Layer is laid as the clad of the helicopter composite material girder construction with right web.
Preferably, it is provided with lightening core on left web laying layer and/or right web the laying layer.
In such scheme preferably, the buried layer is formed by composite plys.
In such scheme preferably, the composite plys neutral surface of the buried layer is parallel to loading direction.
In such scheme preferably, the end of the helicopter composite material girder construction is provided with recess step, with
Miscellaneous equipment or structure connection.
In such scheme preferably, the fibre reinforcement of the helicopter composite material girder construction is carbon fibre fabric.
In such scheme preferably, the fibre reinforcement of the helicopter composite material girder construction is knitted for glass fibre
Thing.
In such scheme preferably, the helicopter composite material girder construction uses resin base RTM epoxy systems.
In such scheme preferably, the resin base RTM epoxy systems include middle temperature epoxy resin and high-temp epoxy tree
At least one of fat.
In such scheme preferably, the helicopter composite material girder construction takes RTM co-curings to be integrally formed.
The helicopter composite material girder construction of RTM technological formings has advantages below：
1st, Varying-thickness web, directly, web is difficult unstable failure to load path, and process implementing is easy；
2nd, surface quality and dimensional accuracy are high；
3rd, compared with traditional aluminium alloy girder construction, loss of weight is up to 20%.
Brief description of the drawings
Fig. 1 is the structural representation of a preferred embodiment of the utility model helicopter composite material girder construction.
Fig. 2 is the buried layer structural representation of the utility model embodiment illustrated in fig. 1.
Fig. 3 is the helicopter composite material girder construction assembling schematic diagram of the utility model embodiment illustrated in fig. 1.
Wherein, 1 is the first skeleton, and 2 be the second skeleton, and 3 be upper laying layer, and 4 be lower laying layer, and 5 be that left web lays layer,
6 be that right web lays layer, and 7 be lightening core.
Embodiment
To make the purpose, technical scheme and advantage of the utility model implementation clearer, below in conjunction with the utility model
Accompanying drawing in embodiment, the technical scheme in the utility model embodiment is further described in more detail.In the accompanying drawings, from beginning
Same or similar element or element with same or like function are represented to same or similar label eventually.Described reality
It is a part of embodiment of the utility model to apply example, rather than whole embodiments.The embodiment described below with reference to accompanying drawing
It is exemplary, it is intended to for explaining the utility model, and it is not intended that to limitation of the present utility model.It is new based on this practicality
Embodiment in type, the every other implementation that those of ordinary skill in the art are obtained under the premise of creative work is not made
Example, belongs to the scope of the utility model protection.Embodiment of the present utility model is described in detail below in conjunction with the accompanying drawings.
In description of the present utility model, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, is for only for ease of description the utility model and simplifies description, rather than indicate or imply and be signified
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to this practicality
The limitation of novel protected scope.
The utility model is described in further details below by embodiment.
The purpose of this utility model is to provide a kind of helicopter composite material girder construction design side of use RTM technological formings
Case, is difficult on Helicopter Main load-carrying construction realize the problem of applying to solve conventional composite materials forming technique.
Composite material beam is designed to a kind of structure type of new skeleton+overcoating laying by the utility model, by structure
Form can be divided into edge strip, web, reinforcement and lower edge strip, as shown in Figure 1；It is divided into buried layer and cladding by installation process
Layer, as shown in Fig. 2 being buried layer structure, as shown in figure 3, being cladding Rotating fields, specifically, the first skeleton 1 and the second skeleton 2
As the buried layer of the helicopter composite material girder construction, the first skeleton 1 and the second skeleton 2 upper and lower ends mutually back to
Edge strip joint face and lower edge strip joint face in bending, formation, by the upper laying layer 3, the cladding institute that coat the upper edge strip joint face
State the lower laying layer 4 of lower edge strip joint face and the left web laying layer 5 in the cladding buried layer centre position and right web paving
If layer 6 is used as the clad of the helicopter composite material girder construction.
With reference to Fig. 2, described girder construction includes built-in type composite skeleton and is coated on the composite plys of outer layer.
Wherein, described built-in type skeleton is I-shaped, and by two pieces of skeletons, docking is formed back-to-back, and its neutral surface is parallel to load side
To；With reference to Fig. 3, the vertical and horizontal laying of described overcoating composite plys along skeleton neutral surface can according to paving location
Be classified as laying layer, 3, lower laying layer 4, left web laying layer 5, right web laying layer 6, wherein left web lays the He of layer 5
Right web laying layer 6 cross section is c-type, and c-type laying layer web is locally hollowed out, and is formed lightening core 7, can be effectively improved web and resist
Failure by shear ability, as shown in Fig. 1 or Fig. 3.
The upper and lower edge strip of girder construction is not limited to flat board, can have more than 1 to sink to meet matching requirements.For meet beam with
The junction flat smooth of other structures, the two ends of beam can be provided with recess step, to accommodate the connection end of other structures, should
Recess step does not influence the thickness of edge strip, by setting the width of web edge strip can be enable internally to be bent to form depression
Step.
Girder construction form is symmetrical relative to neutral surface, but the upper and lower laying direction laid involved by layer, overlay thickness can
Differ.
The number of left web laying layer 5 and the right web laying lightening core of layer 6 is not limited to 2, can for 1 or 2 with
On.
The fibre reinforcement that girder construction is related to is carbon fibre fabric or glass fabric.
Girder construction uses resin base RTM epoxy systems, can be middle temperature epoxy resin, High temperature epoxy resinses.
Girder construction takes RTM co-curings to be integrally formed.
It is last it is to be noted that：Above example is only limited to illustrate the technical solution of the utility model, rather than to it
System.Although the utility model is described in detail with reference to the foregoing embodiments, one of ordinary skill in the art should manage
Solution：It can still be modified to the technical scheme described in foregoing embodiments, or which part technical characteristic is entered
Row equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from each embodiment of the utility model
The spirit and scope of technical scheme.
Claims (10)
1. a kind of helicopter composite material girder construction, it is characterised in that：Including buried layer and clad, by back to the first of setting
Skeleton (1) and buried layer of the second skeleton (2) as the helicopter composite material girder construction, the first skeleton (1) and the second bone
Frame (2) in upper and lower ends mutually back to bending, edge strip joint face and lower edge strip joint face in is formationed, by the cladding upper edge strip
Upper laying layer (3), the lower laying layer (4) of the cladding lower edge strip joint face and the cladding buried layer interposition of joint face
The left web laying layer (5) put and right web lay layer (6) as the clad of the helicopter composite material girder construction.
2. helicopter composite material girder construction as claimed in claim 1, it is characterised in that：The left web laying layer (5) and/
Or it is provided with lightening core (7) on right web laying layer (6).
3. helicopter composite material girder construction as claimed in claim 1, it is characterised in that：The buried layer is spread by composite
Layer is formed.
4. helicopter composite material girder construction as claimed in claim 3, it is characterised in that：The composite paving of the buried layer
Layer neutral surface is parallel to loading direction.
5. helicopter composite material girder construction as claimed in claim 1, it is characterised in that：The helicopter composite material beam knot
The end of structure is provided with recess step, to be connected with miscellaneous equipment or structure.
6. helicopter composite material girder construction as claimed in claim 1, it is characterised in that：The helicopter composite material beam knot
The fibre reinforcement of structure is carbon fibre fabric.
7. helicopter composite material girder construction as claimed in claim 1, it is characterised in that：The helicopter composite material beam knot
The fibre reinforcement of structure is glass fabric.
8. helicopter composite material girder construction as claimed in claim 1, it is characterised in that：The helicopter composite material beam knot
Structure uses resin base RTM epoxy systems.
9. helicopter composite material girder construction as claimed in claim 8, it is characterised in that：The resin base RTM epoxy systems
Including at least one of middle temperature epoxy resin and High temperature epoxy resinses.
10. helicopter composite material girder construction as claimed in claim 1, it is characterised in that：The helicopter composite material beam
Structure takes RTM co-curings to be integrally formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621303414.2U CN206598973U (en) | 2016-11-30 | 2016-11-30 | A kind of helicopter composite material girder construction |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621303414.2U CN206598973U (en) | 2016-11-30 | 2016-11-30 | A kind of helicopter composite material girder construction |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206598973U true CN206598973U (en) | 2017-10-31 |
Family
ID=60149102
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621303414.2U Active CN206598973U (en) | 2016-11-30 | 2016-11-30 | A kind of helicopter composite material girder construction |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206598973U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107966359A (en) * | 2017-11-16 | 2018-04-27 | 彩虹无人机科技有限公司 | A kind of fixture and installation method for testing beam web collapsing load |
| CN112173062A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Composite material integrated frame beam and manufacturing method thereof |
| CN113443170A (en) * | 2021-07-14 | 2021-09-28 | 中国飞机强度研究所 | Combined large-span cross beam structure |
-
2016
- 2016-11-30 CN CN201621303414.2U patent/CN206598973U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107966359A (en) * | 2017-11-16 | 2018-04-27 | 彩虹无人机科技有限公司 | A kind of fixture and installation method for testing beam web collapsing load |
| CN112173062A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Composite material integrated frame beam and manufacturing method thereof |
| CN113443170A (en) * | 2021-07-14 | 2021-09-28 | 中国飞机强度研究所 | Combined large-span cross beam structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN206598973U (en) | A kind of helicopter composite material girder construction | |
| EP2625026B1 (en) | Composite stiffeners for aerospace vehicles | |
| CN101500796B (en) | Laminated construction and structure type structure and manufacture the method being used for aerospace parts | |
| CN103287588B (en) | Frame composite material structural slab is buried in high bearing capacity | |
| US8105523B2 (en) | Reinforcement beam as well as method and fiber laminate for manufacturing the reinforcement beam | |
| US20170001707A1 (en) | Upper joints between outboard wing boxes and wing center sections of aircraft wing assemblies | |
| EP3219602B1 (en) | Tapered height curved composite stringers and corresponding panels | |
| EP2772351B1 (en) | Composite laminated plate having reduced crossply angle | |
| US20060121244A1 (en) | Composite structure with non-uniform density and associated method | |
| CN103661918A (en) | Bonded composite aircraft wing | |
| CN108979951A (en) | A method of wind electricity blade is produced using prefabricated panels | |
| Sharp et al. | Wind blade joints based on non-crimp 3D orthogonal woven Pi shaped preforms | |
| EP2727820B1 (en) | Stringer | |
| CN102378676B (en) | Composite material part with a ramp between two areas | |
| CA2680369A1 (en) | Fibre metal laminate panel | |
| CN104448877A (en) | Composite textiles including spread filaments | |
| Jie et al. | Stiffeners layout design of thin-walled structures with constraints on multi-fastener joint loads | |
| CN105518315A (en) | Joint, and aircraft structure | |
| CN104192292A (en) | Composite integral co-curing aircraft body and processing method | |
| CN109163006A (en) | A kind of link mechanism of composite material and metal bonding | |
| JP2011240925A (en) | Composite structural member with progressive rigidity | |
| JP2011240925A5 (en) | ||
| CN212021859U (en) | Large-size multi-axial composite material bearing plate taking pultruded profile as sandwich | |
| CN104832786B (en) | Helium tank support | |
| CN112173062A (en) | Composite material integrated frame beam and manufacturing method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |