CN103895865A - Novel composite material blade tip structure - Google Patents
Novel composite material blade tip structure Download PDFInfo
- Publication number
- CN103895865A CN103895865A CN201210570045.3A CN201210570045A CN103895865A CN 103895865 A CN103895865 A CN 103895865A CN 201210570045 A CN201210570045 A CN 201210570045A CN 103895865 A CN103895865 A CN 103895865A
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- blade tip
- crossbeam
- covering
- composite material
- chopped fiber
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- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The present invention provides a novel composite material blade tip structure, wherein problems that the whole blade tip is difficultly designed and manufactured and the quality is difficultly controlled are solved. The technical scheme comprises that: short fibers are filled inside the crossbeam of the blade tip region and the region wrapped by skin, and the short fibers are the same as the material of the crossbeam and the inner surface of the skin.
Description
Technical field
The present invention relates to helicopter design field, relate in particular to a kind of advanced composite material blade tip structure.
Background technology
Helicopter rotor blade, by its function and structure feature, can be divided into blade root, blade and blade tip three parts.Because the rotational line speed maximum in blade tip region is the most obvious on the impact of aeroperformance, various blade tip profiles are emerged in an endless stream; Simultaneously, because quiet, the moving trim between the quality in this region autobiography gliding ability and the blade to rotor and the dynamic performance of rotor have the greatest impact, make counterweight and counterweight bearing become the most important component part of blade tip structure.Manufacturing and designing of tradition blade tip structure is mainly manufacturing and designing of counterweight, counterweight bearing and attached fixing, force transferring structure.
Conventional composite materials blade tip version is mainly filled out the structures (or part) such as core 5, counterweight and bearing 6 and is formed (see figure 1) by covering and crossbeam 4, foam.Wherein covering, crossbeam are main load-carrying construction, and foam is filled out core and mainly played filling effect, and they are all the extensions of blade section dependency structure; Counterweight bearing and balance weight assembly are mainly used in the balance of blade and rotor inertia are provided, and the dynamic performance of rotor is also had to material impact.Part is many, and structural interface is many, need carry out special manufacturing and designing; In each Assembly of the parts mold process, contrast locating is more difficult simultaneously, and inconsistent phenomenon etc. easily occurs; These many unfavorable factors, not only make blade tip unit design manufacturing process waste time and energy, and quality is also difficult to be guaranteed, and reliability and maintainability are lower.In addition blade tip is in gentle aerodynamic field region, the maximum centrifugal field of force, and the power transmission design of various parts will become a no small difficult problem together.Modern blade tip profile is more and more thin, and along with the continuous progress of studying, spatial form is more and more complicated; If still manufactured and designed by traditional blade tip version, its difficulty is also inevitable more and more large, is more difficult to control quality.Therefore, need to develop a kind of advanced composite material blade tip version, fundamentally solve blade tip unit design and manufacture the problems such as difficulty, difficult quality control, with meet the continuous blade tip profile Research Requirements making progress.
Summary of the invention
The technical problem to be solved in the present invention: a kind of advanced composite material blade tip structure is provided, solves blade tip unit design and manufacture the problem of difficulty, difficult quality control.
Technical scheme of the present invention: a kind of advanced composite material blade tip structure, comprising:
Intra-zone at blade tip region crossbeam and covering parcel is filled by Chopped fiber, and described Chopped fiber is identical with covering inside face material with crossbeam.
Concrete, crossbeam and the covering in described blade tip region and be filled in crossbeam and covering between Chopped fiber fill out core and after mold pressing, become single component.
Beneficial effect of the present invention: the present invention has removed traditional counterweight bearing, has simplified blade tip structure, makes blade tip structure design, manufacture become simple, and quality can be controlled effectively and ensure, has increased substantially reliability and maintainability; Replace traditional foam to fill out core with Chopped fiber, make the integral structure of blade tip more solid.
Brief description of the drawings
Fig. 1 is conventional composite materials blade tip structural representation.
Fig. 2 is structural representation of the present invention.
Detailed description of the invention
Below the present invention is described in further details.
The invention provides a kind of advanced composite material blade tip structure, as shown in Figure 2, comprising:
The intra-zone wrapping up at blade tip region crossbeam and covering 1 is filled by Chopped fiber 2, and described Chopped fiber 2 is identical with covering 1 inside face material with crossbeam.
Concrete, crossbeam and the covering in described blade tip region and be filled in crossbeam and covering between Chopped fiber fill out core and after mold pressing, become single component.
A kind of advanced composite material blade tip structure of the present invention, remove the blade tip counterweight bearing that tradition needs customized design to manufacture, traditional blade tip designated area foam is filled out to core to be changed into and crossbeam, Chopped fiber resin material that covering inside face is identical, and lay compression molding together with crossbeam, covering, making crossbeam, covering, Chopped fiber in blade tip designated area fill out core becomes a single part.Blade tip counterweight is loaded in the hole of this part assigned address by resin bonding mode.
Owing to having removed traditional counterweight bearing, employing and crossbeam, the Chopped fiber resin material that covering inside face is identical replace the foam in this region and fill out core, and lay compression molding together with crossbeam, covering, making crossbeam, covering, Chopped fiber in blade tip region fill out core becomes without the obvious entirety (becoming a single part) at structural interface and technique interface; Blade tip counterweight is loaded on (size in hole and particular location are fixed according to trim demand) in the hole of overall blade tip assigned address by resin bonding mode.This version, makes the blade tip structure except counterweight become an one-piece parts, must increase substantially reliability and maintainability; Because blade tip covering, crossbeam are the extensions of blade section covering, crossbeam, therefore transmission force property does not have problems simultaneously; Because adopt covering, crossbeam, Chopped fiber to fill out core to lay together the manufacture of compression molding, Chopped fiber is filled out core without special manufacturing and designing, and makes the manufacture of blade tip structure design become more easy, and quality can be controlled effectively and ensure; New blade tip integral structure is more solid, can carry failure-free for various new spatial blade tip designs and support.
Blade unit design process and traditional design process roughly the same, but have been removed the blade tip balance weight assembly design of traditional complexity.In processes process, first lay covering, crossbeam, then only Chopped fiber need be filled up, and compression molding together.The installation of blade tip counterweight, first by quiet, the dynamic balancing measurement of actual blade, in conjunction with the actual size of leads, comprehensively determine quantity and the position that need add counterweight, then bore and leads (the being counterweight) blind hole that diameter is identical at corresponding blade tip position upper surface, in hole, be directly stained with the leads of corresponding weight with resin and hole surface be coated with and put down with resin.
This new composite material blade tip version, has been successfully applied to principle prototype composite material model blade.Through design, manufacture and numerous experimental examinations, show this new composite material blade tip version reliable in structure, manufacture and design easyly, can meet composite material blade Structural Design Requirement completely.
Claims (2)
1. an advanced composite material blade tip structure, is characterized in that, comprising:
Intra-zone at blade tip region crossbeam and covering parcel is filled by Chopped fiber, and described Chopped fiber is identical with covering inside face material with crossbeam.
2. blade tip structure as claimed in claim 1, is characterized in that, crossbeam and the covering in described blade tip region and be filled in crossbeam and covering between Chopped fiber fill out core and after mold pressing, become single component.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210570045.3A CN103895865A (en) | 2012-12-25 | 2012-12-25 | Novel composite material blade tip structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210570045.3A CN103895865A (en) | 2012-12-25 | 2012-12-25 | Novel composite material blade tip structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103895865A true CN103895865A (en) | 2014-07-02 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210570045.3A Pending CN103895865A (en) | 2012-12-25 | 2012-12-25 | Novel composite material blade tip structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103895865A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105269837A (en) * | 2015-10-28 | 2016-01-27 | 北京金风科创风电设备有限公司 | Girder prefabricated part and manufacturing method thereof, and blade and manufacturing method thereof |
| CN113291486A (en) * | 2021-01-06 | 2021-08-24 | 合肥联合飞机科技有限公司 | Balancing method for static balance of helicopter blades |
| CN114030637A (en) * | 2021-11-19 | 2022-02-11 | 中国直升机设计研究所 | Method for cutting girder and girder belt of helicopter |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0786580B1 (en) * | 1996-01-29 | 2003-08-13 | General Electric Company | Multi-component blade for a gas turbine |
| CN101903240A (en) * | 2007-12-18 | 2010-12-01 | 贝尔直升机泰克斯特龙公司 | Rotor blade and manufacture method thereof |
| WO2011026009A1 (en) * | 2009-08-28 | 2011-03-03 | Polystrand, Inc | Thermoplastic rotor blade |
| EP2246260B1 (en) * | 2009-04-29 | 2011-08-31 | EUROCOPTER DEUTSCHLAND GmbH | Rotor blade made of a fibre-reinforced composite material |
| CN102666277A (en) * | 2009-12-21 | 2012-09-12 | 斯奈克玛 | Aircraft propeller blade |
-
2012
- 2012-12-25 CN CN201210570045.3A patent/CN103895865A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0786580B1 (en) * | 1996-01-29 | 2003-08-13 | General Electric Company | Multi-component blade for a gas turbine |
| CN101903240A (en) * | 2007-12-18 | 2010-12-01 | 贝尔直升机泰克斯特龙公司 | Rotor blade and manufacture method thereof |
| EP2246260B1 (en) * | 2009-04-29 | 2011-08-31 | EUROCOPTER DEUTSCHLAND GmbH | Rotor blade made of a fibre-reinforced composite material |
| WO2011026009A1 (en) * | 2009-08-28 | 2011-03-03 | Polystrand, Inc | Thermoplastic rotor blade |
| CN102666277A (en) * | 2009-12-21 | 2012-09-12 | 斯奈克玛 | Aircraft propeller blade |
Non-Patent Citations (1)
| Title |
|---|
| 尹春望: "一种新型复合材料旋翼桨尖结构形式", 《直升机技术》, no. 2, 30 June 2005 (2005-06-30), pages 8 - 11 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105269837A (en) * | 2015-10-28 | 2016-01-27 | 北京金风科创风电设备有限公司 | Girder prefabricated part and manufacturing method thereof, and blade and manufacturing method thereof |
| CN113291486A (en) * | 2021-01-06 | 2021-08-24 | 合肥联合飞机科技有限公司 | Balancing method for static balance of helicopter blades |
| CN114030637A (en) * | 2021-11-19 | 2022-02-11 | 中国直升机设计研究所 | Method for cutting girder and girder belt of helicopter |
| CN114030637B (en) * | 2021-11-19 | 2023-04-25 | 中国直升机设计研究所 | Helicopter girder and girder belt cutting method |
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Application publication date: 20140702 |