CN204527613U - A kind of aircraft D braided composites propeller blade - Google Patents
A kind of aircraft D braided composites propeller blade Download PDFInfo
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- CN204527613U CN204527613U CN201520175907.1U CN201520175907U CN204527613U CN 204527613 U CN204527613 U CN 204527613U CN 201520175907 U CN201520175907 U CN 201520175907U CN 204527613 U CN204527613 U CN 204527613U
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Abstract
The utility model discloses a kind of aircraft D braided composites propeller blade.Blade mold profile is designed, comprises the design at the concrete strengthening position of varying strength and rigidity requirement; Application of carbon fibres three-dimensional preform multiple location combined knitting technology is carried out integrated weaved to blade body and blade specific strengthening position, obtains 3 D stereo braiding structure; After prepared by 3 D stereo braiding structure, make secondary along 3 D stereo braiding structure thickness direction and sew up intensive treatment, obtain secondary sutural texture; With thermosetting resin glue for matrix, vacuum importing and the rapid thermosetting technique combined is adopted to complete the resin compounded operation of described 3 D stereo braiding structure and the preparation of final carbon fiber composite material propeller blade.Multiple 3 D stereo braiding structure, secondary suturing skill and vacuum import the application of the technique that to combine with heatcure, the intensity of propeller blade is strengthened, the production efficiency of blade is effectively improved.
Description
Technical field
The utility model relates to a kind of 3 D stereo weaving carbon fiber composite propeller, is specifically related to a kind of aircraft D braided composites propeller blade.
Background technology
Screw propeller is as the critical component of autogyro or other blimp medium power machinery.Compared with the metal airscrew of traditional material, composite propeller have lightweight, rigidity is large, low vibration, weather resisting property are strong and can the plurality of advantages such as flexible design.The structure of composite propeller comprises propeller hub and blade two parts, and its Leaf is the major part determining whole screw propeller dynamicstability, therefore in recent ten years, a lot of country has carried out the Design and manufacture of the propeller blade of advanced composite material material, and the structure design of composite propeller blade and manufacturing technology are also classified as prior development direction by many countries.
Abroad about the application aspect of composite propeller has many representative instances.In military, composite material main screw is successfully fitted on " extra large king " XZ575 helicopter of Qiuetiq company of Britain production; The ASC-II composite material helicallobe adopting carbon fiber and aramid fiber to make is successfully applied to the SR-22 single-engine aircraft that Cirrus Aircraft Company dispatches from the factory.In civil aircraft, brand-new carbon fiber structural " pioneer " screw propeller of Ha Zeer company (Hartzell) is arranged on Hess base (Husky) general-purpose aircraft of Aviat company, can guarantee that it withstands the flight in outlying mountain area and wilderness.
The all or part of employing fiber-reinforced resin of composite propeller is prepared, in order to improve rigidity, the intensity of composite propeller blade further, the material of high-performance carbon fibre reinforced epoxy based composites is more and more to be applied, screw propeller weight, antifatigue can be alleviated, be convenient to handling maintenance, the multiple effect such as damping noise reduction, life-saving can be realized.But current carbon fiber composite material screw propeller adopts mold pressing or pressure stochastic distribution substantially, there is the weak problem of interlayer of fiber architecture structure, and manufacturing technology requires higher, flow process is loaded down with trivial details comparatively inconvenient.In view of this problem, the utility model adopts brand-new 3 D stereo knitting skill to combine with resin vacuum introducing technology, the vacuum realizing 3 D weaving carbon fiber composite propeller blade is fast curing-formed, 3 D stereo knitting skill effectively improves integral rigidity and the intensity of blade, eliminate Coating combination thin spot, the specific aim structure achieving the composite propeller blade of different application occasion strengthens the object of design, and manufacturing process efficiency is higher.
Utility model content
Technical problem to be solved in the utility model is, a kind of aircraft D braided composites propeller blade is provided, the utility model adopts the structure design of carbon fiber 3 D stereo braiding and vacuum to import fast curing-formed preparation method, to reach the object of propeller blade privileged site mechanical property strengthening, solve the problem of strength weak between blade multiple sheet material layers.
In order to solve above technical matters, the technical solution of the utility model is:
A kind of aircraft D braided composites propeller blade, it comprises inner 3 D stereo braiding structure and dipping and is solidificated in resin bed on described 3 D stereo braiding structure.
Preferably, described 3 D stereo braiding structure comprises the base portion of 3 D stereo braiding structure and the edge enhancing structure of 3 D stereo braiding structure.
Preferably, described 3 D stereo braiding structure also comprises the secondary sutural texture along blade thickness direction.
Preferably, the base portion of described 3 D stereo braiding structure adopts three-dimensional four-way or three-dimensional five to braiding structure, the edge of described 3 D stereo braiding structure strengthen structure adopt three-dimensional five to or three-dimensional four-way braiding structure.
A preparation method for aircraft D braided composites propeller blade, comprises the following steps:
(1) carry out blade mold configuration design according to aerodynamic principle, comprise the design at the concrete strengthening position of varying strength and rigidity requirement;
(2) application of carbon fibres three-dimensional preform multiple location combined knitting technology is carried out integrated weaved to blade body and blade specific strengthening position, obtains 3 D stereo braiding structure;
(3), after prepared by 3 D stereo braiding structure, make secondary along 3 D stereo braiding structure thickness direction and sew up intensive treatment, obtain secondary sutural texture;
(4) with thermosetting resin glue for matrix, the preparation of the resin compounded operation adopting vacuum to import to complete described 3 D stereo braiding structure with the rapid thermosetting technique combined and finally carbon fiber composite material propeller blade.
Preferably, described step (1) Leaf die length is 1-15m, and width is 0.3-3m.
Preferably, the precast body multiple location combined knitting technology in described step (2), adopt in T300, T700 or high-modulus M40 carbon fiber pencil twist yarn one or more.Wherein, T300 refers to that tensile strength is the carbon fiber of 3.5MPa, and the carbon fiber of T700 to be tensile strength be 4.9MPa, M40 is the high modulus carbon fiber of modulus at more than 400GPa.
Preferably, in described step (3), secondary sew up that the stitching yarns of intensive treatment selects in T300, T700 or M40 carbon fiber pencil twist yarn one or more.
Preferably, the fibre weight of described secondary sutural texture accounts for the 5-40% of 3 D stereo braiding structure weight.
Preferably, in described step (4), curing process carries out in large-scale baking oven, and the temperature of heatcure is 80-120 DEG C, and the time of heatcure is 3-6 hour.
Preferably, the degree of vacuum that described vacuum imports is 0.06-0.1MPa.
Preferably, in described step (4), the gum content of the screw blade of preparation is 30-60%.
Preferably, described degree of vacuum is 0.08MPa, and described heat curing temperature is 80 DEG C, and thermal curing time is 3 hours.
Preferably, in described step (4), the gum content of the screw blade of preparation is 40%.
The utility model has following major advantage compared with the technology of preparing of existing composite propeller blade:
(1) according to the mechanical characteristic requirement of aircraft with composite propeller blade, carry out the carbon fabric perform three-dimensional braided structure design of privileged site, by carbon fibre thread type combination, the combination of carbon fibre thread arragement direction, improve blade privileged site strength and stiffness targetedly.
(2) secondary sews up treatment technology.Secondary loop bonding is carried out to above-mentioned 3 D multi-directional stereo weaving precast body through-thickness structure-reinforced, can effectively improve thickness to strength and stiffness.3 D weaving and secondary are sewed up process and are combined, and prepared by the disposable precast body that completes, production efficiency is higher.
(3) adopt vacuum to import and the rapid thermosetting technique combined, complete the preparation of 3 D weaving carbon fiber composite propeller blade, composite product shaping efficiency is higher.
Accompanying drawing explanation
Fig. 1 is the mould structure schematic diagram of propeller blade of the present utility model;
Fig. 2 is the structural representation of 3 D stereo braiding structure of the present utility model;
Fig. 3 is secondary sutural texture schematic diagram of the present utility model.
Wherein, 1, blade body, 2, blade edge reinforcing section, 3, the edge of 3 D stereo braiding structure strengthens structure, 4, the base portion of 3 D stereo braiding structure, 5, secondary sutural texture.
Detailed description of the invention
Below in conjunction with accompanying drawing, embodiment of the present utility model is further described.
Embodiment one
Fig. 1 is the mould structure schematic diagram of propeller blade of the present utility model, and mould comprises blade body 1 and is arranged on the blade edge reinforcement structure 2 at blade body edge.The 3 D stereo braiding structure of propeller blade of the present utility model is namely according to the mould structure knitting forming in Fig. 1.
As shown in Figures 2 and 3, a kind of aircraft D braided composites propeller blade, it comprises inner 3 D stereo braiding structure and dipping and is solidificated in resin bed on described 3 D stereo braiding structure, and described 3 D stereo braiding structure comprises the base portion 4 of 3 D stereo braiding structure, the edge of 3 D stereo braiding structure strengthens structure 3 and the secondary sutural texture 5 along blade thickness direction.
3 D stereo braiding is carried out based on the mould in Fig. 1, wherein the braiding scheme of blade interior main body is: the base portion 4 of 3 D stereo braiding structure adopts three-dimensional four-way to weave process, one or both combinations in T300, T700 carbon fiber selected by yarn, the edge of 3 D stereo braiding structure strengthens structure 3 and adopts three-dimensional five to braiding process, and one or more combinations in T300, T700 or M40 carbon fiber selected by yarn.Screw blade leaf length after overall 3 D weaving is 2m, and width is 0.5m.The secondary 3 D stereo braiding structure of knitting forming being proceeded thickness direction sews up process, and select T700 carbon fiber as enhancing yarn, staples proportion accounts for 20% of integral prefabricated body fiber proportion, and secondary sutural texture schematic diagram as shown in Figure 3.
Carbon fiber blade precast body after 3 D weaving adopts epoxy resin adhesive liquid to be raw matrix materials, and adopt VARI vacuum introducing technology to make glue fully flood with blade precast body, the degree of vacuum of whole dipping recombination process remains on 0.08MPa.Blade after insulating varnish is in 80 DEG C of solidifications, 3 hours aftershapings, and gum content remains on 40%.
Embodiment two
3 D stereo braiding is carried out based on the core in Fig. 1, wherein the braiding scheme of blade interior main body is: the base portion 4 of 3 D stereo braiding structure adopts three-dimensional five to braiding process, T300 carbon fiber selected by yarn, the edge of 3 D stereo braiding structure strengthens structure 3 and adopts three-dimensional four-way to weave process, blade edge knitting yarn line selection one or both combinations in T300, T700.Screw blade leaf length after overall 3 D weaving is 4m, and width is 1m.The secondary precast body of knitting forming being proceeded thickness direction sews up process, and select T300 carbon fiber as enhancing yarn, staples proportion accounts for 15% of integral prefabricated body fiber proportion, and sutural texture schematic diagram as shown in Figure 3.
Carbon fiber blade precast body after 3 D weaving adopts epoxy resin adhesive liquid to be raw matrix materials, and adopt VARI vacuum introducing technology to make glue fully flood with blade precast body, the degree of vacuum of whole dipping recombination process remains on 0.1MPa.Blade after insulating varnish is in 90 DEG C of solidifications, 2.5 hours aftershapings, and gum content remains on 35%.
Embodiment three
3 D stereo braiding is carried out based on the core in Fig. 1, wherein the braiding scheme of blade interior main body is: the base portion 4 of 3 D stereo braiding structure adopts three-dimensional four-way to weave process, T700 carbon fiber selected by yarn, the edge of 3 D stereo braiding structure strengthens structure 3 and adopts three-dimensional five to braiding process, blade edge knitting yarn line selection one or both combinations in T300, T700.Screw blade leaf length after overall 3 D weaving is 3m, and width is 0.6m.The secondary precast body of knitting forming being proceeded thickness direction sews up process, and select T700 carbon fiber as enhancing yarn, staples proportion accounts for 25% of integral prefabricated body fiber proportion, and sutural texture schematic diagram as shown in Figure 3.
Carbon fiber blade precast body after 3 D weaving adopts epoxy resin adhesive liquid to be raw matrix materials, and adopt VARI vacuum introducing technology to make glue fully flood with blade precast body, the degree of vacuum of whole dipping recombination process remains on 0.08MPa.Blade after insulating varnish is in 80 DEG C of solidifications, 2 hours aftershapings, and gum content remains on 38%.
By reference to the accompanying drawings detailed description of the invention of the present utility model is described although above-mentioned; but the restriction not to utility model protection scope; one of ordinary skill in the art should be understood that; on the basis of the technical solution of the utility model, those skilled in the art do not need to pay various amendment or distortion that creative work can make still in protection domain of the present utility model.
Claims (4)
1. an aircraft D braided composites propeller blade, is characterized in that: comprise inner 3 D stereo braiding structure and dipping and be solidificated in resin bed on described 3 D stereo braiding structure.
2. propeller blade according to claim 1, is characterized in that: the edge of base portion and 3 D stereo braiding structure that described 3 D stereo braiding structure comprises 3 D stereo braiding structure strengthens structure.
3. propeller blade according to claim 2, is characterized in that: described 3 D stereo braiding structure also comprises the secondary sutural texture along blade thickness direction.
4. propeller blade according to claim 3, it is characterized in that: the base portion of described 3 D stereo braiding structure adopts three-dimensional four-way or three-dimensional five to braiding structure, the edge of described 3 D stereo braiding structure strengthen structure adopt three-dimensional five to or three-dimensional four-way braiding structure.
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| CN201520175907.1U CN204527613U (en) | 2015-03-26 | 2015-03-26 | A kind of aircraft D braided composites propeller blade |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104743099A (en) * | 2015-03-26 | 2015-07-01 | 北京勤达远致新材料科技股份有限公司 | Three-dimensional braided composite material propeller blade for airplane and manufacturing method of propeller blade |
| CN105252786A (en) * | 2015-10-14 | 2016-01-20 | 哈尔滨飞机工业集团有限责任公司 | Method for preventing collapse of honeycombs of sandwich parts |
| CN106567111A (en) * | 2015-10-13 | 2017-04-19 | 河南卓尔航空科技有限公司 | Metal electroplating edge covering process for carbon fiber composite propeller |
| CN106652718A (en) * | 2015-11-04 | 2017-05-10 | 宜兴市中碳科技有限公司 | Irregular superhard carbon fiber plate for aviation model |
| CN107472512A (en) * | 2017-08-01 | 2017-12-15 | 西华酷农无人机产业园运营有限公司 | A kind of reinforced propeller of unmanned plane |
| RU2755419C1 (en) * | 2020-12-17 | 2021-09-15 | Виктор Александрович Егоров | Method for increasing the service life of propellers of marine and river floating vehicles by the method for multilayer alloying |
-
2015
- 2015-03-26 CN CN201520175907.1U patent/CN204527613U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104743099A (en) * | 2015-03-26 | 2015-07-01 | 北京勤达远致新材料科技股份有限公司 | Three-dimensional braided composite material propeller blade for airplane and manufacturing method of propeller blade |
| CN106567111A (en) * | 2015-10-13 | 2017-04-19 | 河南卓尔航空科技有限公司 | Metal electroplating edge covering process for carbon fiber composite propeller |
| CN105252786A (en) * | 2015-10-14 | 2016-01-20 | 哈尔滨飞机工业集团有限责任公司 | Method for preventing collapse of honeycombs of sandwich parts |
| CN106652718A (en) * | 2015-11-04 | 2017-05-10 | 宜兴市中碳科技有限公司 | Irregular superhard carbon fiber plate for aviation model |
| CN107472512A (en) * | 2017-08-01 | 2017-12-15 | 西华酷农无人机产业园运营有限公司 | A kind of reinforced propeller of unmanned plane |
| RU2755419C1 (en) * | 2020-12-17 | 2021-09-15 | Виктор Александрович Егоров | Method for increasing the service life of propellers of marine and river floating vehicles by the method for multilayer alloying |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
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Effective date of registration: 20220324 Address after: 251100 Room 305, 3 / F, block a, Zhongguancun Science and Technology City, Qilu high tech Development Zone, Qihe County, Dezhou City, Shandong Province Patentee after: Shandong Guangyuan new material technology Co.,Ltd. Address before: 102200 No. 2222, building 2, No. 7, Chuangxin Road, science and Technology Park, Changping District, Beijing Patentee before: BEIJING QINDA YUANZHI NEW MATERIAL TECHNOLOGY Co.,Ltd. |
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| TR01 | Transfer of patent right |