JPS632796A - Composite material blade - Google Patents
Composite material bladeInfo
- Publication number
- JPS632796A JPS632796A JP14727386A JP14727386A JPS632796A JP S632796 A JPS632796 A JP S632796A JP 14727386 A JP14727386 A JP 14727386A JP 14727386 A JP14727386 A JP 14727386A JP S632796 A JPS632796 A JP S632796A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- spiral
- shank
- lattice
- spar
- 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.)
- Granted
Links
- 239000002131 composite material Substances 0.000 title claims description 26
- 239000002184 metal Substances 0.000 claims description 13
- 239000000853 adhesive Substances 0.000 claims description 5
- 230000001070 adhesive effect Effects 0.000 claims description 5
- 238000006243 chemical reaction Methods 0.000 description 5
- 230000007246 mechanism Effects 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000945 filler Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 210000004894 snout Anatomy 0.000 description 1
Landscapes
- Polishing Bodies And Polishing Tools (AREA)
- Shafts, Cranks, Connecting Bars, And Related Bearings (AREA)
Abstract
(57)【要約】本公報は電子出願前の出願データであるた
め要約のデータは記録されません。(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.
Description
【発明の詳細な説明】
〔産業上の利用分野〕
この発明は、例えばＦ ＲＰ ’ＩＪ等、複合材で製作
したブレードシェルと翼桁を有する航空機用プロペラブ
レードに関するものであり、特にブレードをハブおよび
可変ピンチ機構と接続するために使用される金属部材と
複合材のブレードとの結合部の改良に関するものである
。[Detailed Description of the Invention] [Industrial Application Field] The present invention relates to an aircraft propeller blade having a blade shell and a wing spar made of composite materials, such as FRP'IJ, and in particular, to and an improvement in the connection between a metal member and a composite blade used to connect a variable pinch mechanism.
従来、複合材料、特にＦＲＰ製のブレードは金属製ブレ
ードに比較して軽量で、ブレードに働く遠心力、遠心捩
りモーメントが小で、ブレードを支持するハブ、可変ピ
ンチ機構の荷重負担が小さい、また複合材ブレードは、
ブレードの剛性、質量分布が自由に設計できるので固有
振動数の調整が容易でブレードの製造および修理が容易
、安価である等の理由で多く用いられている。Conventionally, blades made of composite materials, especially FRP, are lighter than metal blades, have less centrifugal force and centrifugal torsion moment acting on the blade, and have less load on the hub that supports the blade and the variable pinch mechanism. The composite blade is
It is widely used because the rigidity and mass distribution of the blade can be freely designed, the natural frequency can be easily adjusted, the blade is easy to manufacture and repair, and it is inexpensive.
しかし、複合材ブレードもシェルや翼桁は複合材で製作
できても、シャンク部ではブレードをハブおよび可変ピ
フチａ構に接続する関係上、金属材料の部材を複合材ブ
レードと結合する必要が生じる０例えば、ブレードをピ
ッチ変換するための偏心ビンや歯車等をブレードに固定
する必要があるが、ピンや歯車を複合材にすることは硬
度や精度が不足し製作不適であり、またブレードをハブ
に固定し、ブレードがピンチ変換軸まわりに回転できる
ようベアリングを複合材ブレードに装着する必要がある
が、ベアリングレースは硬度、寸法精度上ＦＲＰによる
製作は国難である。これらのことからブレードシャンク
部では金属部材と複合材ブレードとをボルト等で固定結
合している。However, even if the shell and wing spar of a composite blade can be made of composite material, it is necessary to connect a metal member to the composite blade at the shank part in order to connect the blade to the hub and variable pitch a structure. 0 For example, it is necessary to fix an eccentric pin or gear to the blade to change the pitch of the blade, but making pins and gears from composite materials lacks hardness and precision, making it unsuitable for manufacturing. It is necessary to attach a bearing to the composite blade so that the blade can rotate around the pinch conversion axis, but manufacturing the bearing race from FRP is a national problem due to its hardness and dimensional accuracy. For these reasons, the metal member and the composite blade are fixedly connected to each other by bolts or the like in the blade shank portion.
しかし、ボルト等による結合ではシャンク部の構造が複
雑となり、機械加工工数も増加し、且つボルト用孔等に
応力集中が発生しＦＲＰの有する高強度特性を十分発揮
させること力咄来ない。更にブレードの強度が低下する
恐れもある。However, connecting with bolts or the like complicates the structure of the shank portion, increases the number of machining steps, and causes stress concentration in bolt holes, etc., making it difficult to fully utilize the high strength characteristics of FRP. Furthermore, the strength of the blade may be reduced.
如上の問題に鑑み本発明では極力ボルト結合を排し、ス
リーブとガイドで翼桁シャンク部を挟持固定する簡単な
構造で、ブレードと金属部材を６育実に結合する複合材
ブレードの提供を目的とするものである。In view of the above-mentioned problems, the present invention aims to provide a composite blade that connects the blade and the metal member in a simple structure in which the blade spar shank is clamped and fixed between the sleeve and the guide, eliminating bolt connections as much as possible. It is something to do.
（問題点を解決するための手段）
本発明は、根元端にフランジを設けた複合材翼桁の中空
筒状シャンク部内外周に螺旋状または格子状凹凸を形成
し、該シャンク部内側へ根元端にフランジを有し外周面
に前記翼桁シャンク内周の螺旋または格子に嵌合する螺
旋または格子を設けた複合材製または金属製のガイドを
挿入し、また前記翼桁シャンク部外側へは根元端にフラ
ンジを有し内周面に前記翼桁シャンク外周面の螺旋また
は格子に嵌合する螺旋または格子を設けた金属製スリー
ブを当てがい、それぞれ翼桁／ヤンク部とフランジの間
に接着剤を介して一体に挟持固定した複合材ブレードを
要旨とし
■ シャンク部とスリーブ螺旋または格子結合によって
遠心力および捩りモーメントを伝達する機械的結合。(Means for solving the problem) The present invention forms spiral or lattice-like unevenness on the inner and outer circumferences of the hollow cylindrical shank part of the composite wing spar with a flange at the root end, and A guide made of composite material or metal having a flange at the end and a spiral or lattice on the outer peripheral surface that fits into the spiral or lattice on the inner circumference of the spar shank is inserted, and a guide made of composite material or metal is inserted to the outside of the spar shank. A metal sleeve with a flange at the root end and a spiral or lattice on the inner circumferential surface that fits into the spiral or lattice on the outer circumferential surface of the wing spar shank is applied, and bonded between the wing spar/yank part and the flange, respectively. ■ A mechanical connection that transmits centrifugal force and torsional moment through a spiral or lattice connection between the shank and sleeve.
■ ガイドに働く遠心力によって翼桁シャンク部をスリ
ーブに押つける機械的結合。■ Mechanical connection that presses the wing spar shank against the sleeve using centrifugal force acting on the guide.
■ シャンク部とスリーブの接着結合、ガイドとシャン
ク部との接着結合。■ Adhesive connection between the shank and sleeve, and adhesive connection between the guide and shank.
■ シャンク部とスリーブ間の接着がｆｆ１ｌ＋離して
もガイドによりシャンク部が半径方向の変形を阻止され
上記機械的結合を補償する。(2) Even if the adhesion between the shank part and the sleeve becomes ff1l+ separated, the guide prevents the shank part from being deformed in the radial direction and compensates for the above-mentioned mechanical connection.
等の特徴を有している。It has the following characteristics.
以下図面に示す実施例に基づいて本発明の複合材ブレー
ドについてさらに説明する。The composite blade of the present invention will be further explained below based on the embodiments shown in the drawings.
第１図はブレードシャンク部を中心とした断面を示す平
面図、第２図は第１図のＡ−Ａ断面図である。1 is a plan view showing a cross section centered on the blade shank portion, and FIG. 2 is a sectional view taken along the line AA in FIG. 1.
図において、（１）はブレードを形成する複合材シェル
で翼型をしている。（２）はシェル（１）内に充填され
る詰め物、（３）はシェル＋１１内の長手方向に設けら
れた複合材製の翼桁で、その基部にはフランジ側を有し
、中空筒状のシャンク部（９）の内外１５１面には左ネ
ジの螺旋状凹凸Ｑｍを形成している。（４）は−端にフ
ランジａ１を有する中空筒状ガイドで外周面に翼桁（３
）の螺旋０３に嵌合する螺旋０Ｑが設けである。In the figure, (1) is a composite shell forming a blade, which has an airfoil shape. (2) is a filler filled in the shell (1), and (3) is a wing spar made of composite material provided in the longitudinal direction inside the shell +11, which has a flange side at its base and has a hollow cylindrical shape. A left-handed spiral unevenness Qm is formed on the inner and outer 151 surfaces of the shank portion (9). (4) is a hollow cylindrical guide with a flange a1 at the negative end, and a wing spar (3
The spiral 0Q that fits into the spiral 03 of ) is provided.
ガイド（４）は金属材料で加工してもよいが、複合材で
成形してブレードの重量軽減をはかってもよい。The guide (4) may be made of a metal material, but may also be formed of a composite material to reduce the weight of the blade.
（５）は−端にフランジαすを有する中空筒状の金属製
スリーブであり、その内周面に翼ｔｔｉ （３１の螺旋
状凹凸Ｑｌに嵌合する螺旋Ｇ（ｌを設けている。(5) is a hollow cylindrical metal sleeve having a flange α at the negative end, and a spiral G(l) that fits into the spiral unevenness Ql of the wing Tti(31) is provided on the inner circumferential surface of the sleeve.
（６）はブレード基部のフランジθη■Ｇ’９に貫通固
定されたブレードピッチ変更用の偏心ビン。＋７）はブ
レードをハブ（図示せず）に回転可能に支承するベアリ
ング。（８）はブレードのピッチ変換軸。（９）はブレ
ードを保持する領域でシャンク部と呼ばれる。(6) is an eccentric pin for changing the blade pitch that is fixed through the flange θη■G'9 at the base of the blade. +7) is a bearing that rotatably supports the blade on a hub (not shown). (8) is the pitch conversion axis of the blade. (9) is a region that holds the blade and is called a shank portion.
Ｑｌは翼桁（３）、ガイド（４）、スリーブ（５）の軸
方向の結合部、０υは上記の周方向の結合部である。Ql is the axial connection between the wing spar (3), guide (4), and sleeve (5), and 0υ is the circumferential connection.
なお、翼桁（３）の中空筒状シャンク部（９）の内外周
面の螺旋状凹凸、これに嵌合する中空筒状ガイド（４）
に設ける螺旋、スリーブ（５）の内周面に設ける螺旋状
凹凸は必ずしも螺旋でなくても例えば格子状凹凸でもよ
い。In addition, the spiral unevenness on the inner and outer circumferential surfaces of the hollow cylindrical shank portion (9) of the wing spar (3), and the hollow cylindrical guide (4) that fits therein.
The spiral provided on the sleeve (5) and the spiral unevenness provided on the inner circumferential surface of the sleeve (5) do not necessarily have to be a spiral, and may be, for example, a lattice-like unevenness.
第３図に格子状凹凸を設けたスリーブ（５）の断面図を
示す。FIG. 3 shows a sectional view of the sleeve (5) provided with lattice-like unevenness.
上記の如く、本発明では軸方向の結合部０ωを螺旋また
は格子状凹凸で構成しており、且つ翼桁（３）、ガイド
（４）、スリーブ（５）の各接触部に接着剤を貼付して
結合される。As described above, in the present invention, the axial joint portion 0ω is formed of a spiral or grid-like unevenness, and adhesive is applied to each contact portion of the wing spar (3), guide (4), and sleeve (5). and are combined.
以上の構成よりして、ブレードの遠心力は結合部α０で
ピンチ変換軸（８）から放射状に展開しスリーブ（５）
に伝達されるので、ガイド（４）に作用する遠心力によ
って翼桁（３）をスリーブ（５）に押付け、翼桁（３）
の引抜けを防止できる。また翼桁（３）とスリーブ（５
）間の接着剤が剥離しても、ガイド（４）により翼桁（
３）を規定位置にとどめ、ブレードに働く遠心力および
モーメントの伝達を確保する。With the above configuration, the centrifugal force of the blade develops radially from the pinch conversion axis (8) at the joint α0, and
Since the centrifugal force acting on the guide (4) presses the wing spar (3) against the sleeve (5), the wing spar (3)
can be prevented from being pulled out. Also, the wing spar (3) and sleeve (5)
) even if the adhesive between the blades (
3) remains in the specified position to ensure the transmission of centrifugal force and moment acting on the blade.
本発明では複合材ブレードで発生する遠心力を翼桁（３
）、スリーブ（５）、ベアリング（７）を介してハブに
伝達する。In the present invention, the centrifugal force generated in the composite blade is
), sleeve (5), and bearing (7) to the hub.
また、ブレードで発生するピッチ変換軸（８）まわりの
遠心捩りモーメントを翼桁（３）、ガイド（４）、スリ
ーブ（５）、偏心ピン（６）を介して可変ピッチ機構に
伝達する。その他の力およびモーメントは翼桁（３）、
スリーブ（５）、ベアリング（７）を介してハブに伝達
する。Further, the centrifugal torsional moment generated in the blade around the pitch conversion axis (8) is transmitted to the variable pitch mechanism via the blade spar (3), guide (4), sleeve (5), and eccentric pin (6). Other forces and moments are wing spars (3);
It is transmitted to the hub via the sleeve (5) and bearing (7).
以上のように本発明では、幾重もの伝達手段を有してい
るので複合材ブレードから金属部材へ荷重を確実に伝達
することができ、しかもボルト孔等の如く応力集中が発
生する機構を可及的に排除したので、ブレードの強度が
低下する恐れがない。As described above, the present invention has multiple transmission means, so it is possible to reliably transmit the load from the composite blade to the metal member, and it is also possible to use mechanisms that cause stress concentration, such as bolt holes. Since it is completely eliminated, there is no risk of reducing the strength of the blade.
第１図は本発明に係る複合材ブレードのソヤンク部構造
例を示す一部断面平面図。
第２図は第１図のＡ−Ａ％面図。
第３図は本発明の他の実施例に係るスリーブの断面平面
図である。
１ニジエル、２：詰め吻、３：翼桁、４；ガイド、５ニ
スリーブ、６：偏心ビン、７：へアリング、８：ピッチ
変換軸、９：シャンク部、１０，１１：結合部、１２．
１５．１７ ：フランジ、１３．１４．１６：ｇ、旋状
または格子状凹凸
第 １ 図FIG. 1 is a partially sectional plan view showing an example of the structure of a soyank portion of a composite material blade according to the present invention. FIG. 2 is a sectional view taken along the line A-A in FIG. 1. FIG. 3 is a cross-sectional plan view of a sleeve according to another embodiment of the present invention. 1 Nizier, 2: Stuffed snout, 3: Wing spar, 4: Guide, 5 Ni sleeve, 6: Eccentric bottle, 7: Hair ring, 8: Pitch conversion shaft, 9: Shank part, 10, 11: Joint part, 12.
15.17: Flange, 13.14.16: g, spiral or lattice irregularities Fig. 1
Claims (1)
状シャンク部の内外周に螺旋状または格子状凹凸を形成
し、該シャンク部内側へ根元端にフランジを有し外周面
に前記翼桁シャンク内周の螺旋または格子に嵌合する螺
旋または格子を設けた複合材製または金属製のガイドを
挿入し、また前記翼桁シャンク部外側へは根元端にフラ
ンジを有し内周面に前記翼桁シャンク外周面の螺旋また
は格子に嵌合する螺旋または格子を設けた金属製スリー
ブを当てがい、それぞれ翼桁シャンク部とフランジの間
に接着剤を介して一体に挟持固定したことを特徴とする
複合材ブレード。(1) A spiral or lattice-like unevenness is formed on the inner and outer periphery of the hollow cylindrical shank of a composite wing spar with a flange at the root end, and a flange is provided at the root end and a concavo-convex surface on the inner side of the shank. A guide made of composite material or metal having a spiral or lattice that fits into the spiral or lattice on the inner periphery of the spar shank is inserted, and a guide made of composite material or metal is inserted to the outside of the spar shank portion and has a flange at the root end and a guide on the inner periphery. A metal sleeve provided with a spiral or lattice that fits into the spiral or lattice on the outer circumferential surface of the spar shank is applied to the surface, and each is clamped and fixed together with an adhesive between the spar shank and the flange. A composite blade featuring:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14727386A JPS632796A (en) | 1986-06-23 | 1986-06-23 | Composite material blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14727386A JPS632796A (en) | 1986-06-23 | 1986-06-23 | Composite material blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS632796A true JPS632796A (en) | 1988-01-07 |
| JPH0438637B2 JPH0438637B2 (en) | 1992-06-25 |
Family
ID=15426480
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP14727386A Granted JPS632796A (en) | 1986-06-23 | 1986-06-23 | Composite material blade |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS632796A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021157675A1 (en) * | 2020-02-04 | 2021-08-12 | Hapsmobile Inc. | Propeller blade-to-hub coupler for an unmanned aerial vehicle |
-
1986
- 1986-06-23 JP JP14727386A patent/JPS632796A/en active Granted
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021157675A1 (en) * | 2020-02-04 | 2021-08-12 | Hapsmobile Inc. | Propeller blade-to-hub coupler for an unmanned aerial vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH0438637B2 (en) | 1992-06-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6676080B2 (en) | Composite airfoil assembly | |
| US5738494A (en) | Optimized composite flexbeam for helicopter rotors | |
| US4626172A (en) | Variable-pitch multi-blade propeller incorporating individually dismountable blades made of composite materials, process for manufacturing such blades and blades thus produced | |
| US5690474A (en) | Optimized composite flexbeam for helicopter tail rotors | |
| US4877376A (en) | Attachment of a rotor blade of fiber reinforced plastic to a metal rotor hub | |
| CA2667469C (en) | Propeller blade retention | |
| US4087203A (en) | Cross beam rotor | |
| JP3801647B2 (en) | Helicopter rotor composite cuff structure | |
| US9169011B2 (en) | Rotor with blades including outer blade shell and inner structural member | |
| US20020164251A1 (en) | Composite rotor blade and method of manufacture | |
| US8662847B2 (en) | Rotor blade with control tube | |
| WO1998030446A2 (en) | Variable pitch aircraft propeller | |
| WO1998030446A9 (en) | Variable pitch aircraft propeller | |
| GB2029911A (en) | Wind turbine blade tetention device | |
| US10717516B2 (en) | Composite propulsor blade support structure and system | |
| JPH0536280B2 (en) | ||
| US5619797A (en) | Flow-straightener vane for counter-torque device with ducted rotor and ducted flow-straightening stator, for helicopter | |
| US4227859A (en) | Rotor for a gyroplane | |
| JPS632796A (en) | Composite material blade | |
| JPH057240B2 (en) | ||
| EP2554475B1 (en) | Planar flexbeam unit | |
| JPH06247390A (en) | Shank portion structure of composite blade | |
| EP3929077B1 (en) | Rotor for an aircraft capable of hovering | |
| USRE30713E (en) | Cross beam rotor | |
| EP3659914A1 (en) | Rotor for a hover-capable aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| EXPY | Cancellation because of completion of term |