JP7015151B2 - Wings - Google Patents

Wings Download PDF

Info

Publication number
JP7015151B2
JP7015151B2 JP2017222663A JP2017222663A JP7015151B2 JP 7015151 B2 JP7015151 B2 JP 7015151B2 JP 2017222663 A JP2017222663 A JP 2017222663A JP 2017222663 A JP2017222663 A JP 2017222663A JP 7015151 B2 JP7015151 B2 JP 7015151B2
Authority
JP
Japan
Prior art keywords
main girder
wing
lower outer
outer skins
root
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
Application number
JP2017222663A
Other languages
Japanese (ja)
Other versions
JP2019094796A (en
Inventor
宏樹 若林
明栄 奥
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Toray Carbon Magic Co Ltd
Original Assignee
Toray Carbon Magic Co Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Toray Carbon Magic Co Ltd filed Critical Toray Carbon Magic Co Ltd
Priority to JP2017222663A priority Critical patent/JP7015151B2/en
Publication of JP2019094796A publication Critical patent/JP2019094796A/en
Application granted granted Critical
Publication of JP7015151B2 publication Critical patent/JP7015151B2/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Landscapes

  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

本発明は、形状と構造を改良した翼に関し、比較的大型の風洞実験用設備等に好適な翼に関するものである。 The present invention relates to a wing having an improved shape and structure, and is suitable for a relatively large wind tunnel experimental facility or the like.

近年、各種用途に用いられる翼の性能向上や効率向上のため、使用される翼には非常に複雑な形状や構造のものも採用されており、かつ、多様なデザイン構成を持ったものや特殊な製法を採用したものも知られている（例えば、特許文献１～７）。 In recent years, in order to improve the performance and efficiency of wings used in various applications, very complicated shapes and structures have been adopted for the wings used, and those with various design configurations and special ones. There are also known products that employ various manufacturing methods (for example, Patent Documents 1 to 7).

周知の翼形状、翼構造はさまざまな材料を用いて製造が可能であり、それらの材料としては、例えば、アルミニウム、チタン、鉄鋼、繊維強化複合材料（ガラス繊維、炭素繊維、アラミド繊維を用いた複合材料等）、木材等が使用可能である。とくに近年、動力エネルギーの効率化のため比較的大型の翼には軽量化が求められ、繊維強化複合材料（ガラス繊維、炭素繊維、アラミド繊維を用いた複合材料等）の採用が進んでいる。 Well-known wing shapes and wing structures can be manufactured using various materials, such as aluminum, titanium, steel, and fiber reinforced composite materials (glass fiber, carbon fiber, and aramid fiber). Composite materials, etc.), wood, etc. can be used. In particular, in recent years, relatively large wings are required to be lighter in order to improve the efficiency of power energy, and fiber reinforced composite materials (composite materials using glass fiber, carbon fiber, aramid fiber, etc.) are being adopted.

特開２０１１－０１１４７３号公報Japanese Unexamined Patent Publication No. 2011-011473 特開２００１－１２９８４４号公報Japanese Unexamined Patent Publication No. 2001-129844 特開２００２－２２７７９６号公報Japanese Unexamined Patent Publication No. 2002-227996 特開２００２－１６１８９３号公報Japanese Unexamined Patent Publication No. 2002-161893 特開２０１１－１２７４８１号公報Japanese Unexamined Patent Publication No. 2011-127418 特開２０１０－２０３４３５号公報Japanese Unexamined Patent Publication No. 2010-203435 特開２０１６－１２５４４１号公報Japanese Unexamined Patent Publication No. 2016-12541

比較的大型の翼を軽量化するためには、必要な強度や剛性を確保しつつ、構成部材間の連結や接合を確実に行えることや作業容易化のために構造を簡素化することが求められる。そのためには、構成部材の点数を極力少ない点数に抑え、その条件下で、連結や接合の確実性を確保しつつ、捩じれ等の複雑な翼形状にも容易に対応できるようにすることが要求される。 In order to reduce the weight of relatively large wings, it is necessary to secure the necessary strength and rigidity, ensure connection and joining between components, and simplify the structure to facilitate work. Be done. For that purpose, it is necessary to keep the number of constituent members as low as possible, and under those conditions, to ensure the certainty of connection and joining, and to easily cope with complicated blade shapes such as twisting. Will be done.

そこで本発明の課題は、上記のような実情に鑑み、少ない構成部材点数で確実に必要な連結や接合を行うことができ、捩じれ等の複雑な翼形状にも容易に対応できるようにした、とくに主要構成部材が繊維強化プラスチックからなる比較的大型の翼に適用して好適な翼形状と構造を提供することにある。 Therefore, the subject of the present invention is that, in view of the above circumstances, necessary connection and joining can be reliably performed with a small number of constituent members, and complicated blade shapes such as twisting can be easily dealt with. In particular, it is intended to be applied to a relatively large wing whose main component is made of fiber reinforced plastic to provide a suitable wing shape and structure.

上記課題を解決するために、本発明に係る翼は、翼形状を形成する上下外皮と、ロータ軸側に接続され前記上下外皮が連結される翼根部材と、前記上下外皮の内側に配設されて該上下外皮に接合され前記翼根部材を貫通して延びる主桁とを有し、前記翼根部材と前記主桁との接合部が、主桁根元側から先端側に向けて先細りとなるテーパー形状に構成されていることを特徴とするものからなる。 In order to solve the above problems, the wing according to the present invention is disposed inside the upper and lower outer skins forming the blade shape, the wing root member connected to the rotor shaft side and connected to the upper and lower outer skins, and the upper and lower outer skins. It has a main girder that is joined to the upper and lower outer skins and extends through the wing root member, and the joint portion between the wing root member and the main girder tapers from the root side to the tip side of the main girder. It is characterized by being configured in a tapered shape.

このような本発明に係る翼においては、回転駆動手段としてのロータ軸へと接続または連結される翼の主要構成部材は、上下外皮と、翼根部材と、主桁とからなる。上下外皮の内側に配設されて該上下外皮に接合される主桁は、翼根部材を貫通して延び、翼根部材と主桁との接合部は、主桁根元側から先端側に向けて先細りとなるテーパー形状に構成されている。ロータ軸からの回転駆動力が翼根部材を介して上下外皮と主桁に伝達され、主桁およびそれに接続された翼の主外形形状を形成する上下外皮が回転される際、その遠心力が翼根部材に加わることになるが、翼根部材と主桁との接合部が先細りテーパー形状に構成されていることにより、遠心力が効率よく翼根部材に伝達されるとともに、その遠心力が接合部におけるテーパー形状がより締まる方向に（翼根部材の内面側テーパー形状部と主桁の外面側テーパー形状部が互いに食い込み締め合う方向に）作用するので、この接合部における接合の確実性が向上される。その結果、少ない構成部材で翼に要求される必要な強度や剛性が容易に確保されつつ、構成部材間の接合が確実にかつ容易に行えるようになる。また、翼根部材と主桁との接合が特別な付加部材を要することなく、翼根部材と主桁を直接接合することで達成でき、少ない構成部材点数で目標とする接合構造を実現できるとともに、翼全体の軽量化にも寄与できることになる。 In such a wing according to the present invention, the main constituent members of the wing connected to or connected to the rotor shaft as the rotation driving means include upper and lower exodermis, wing root member, and main girder. The main girder disposed inside the upper and lower outer skins and joined to the upper and lower outer skins extends through the wing root member, and the joint portion between the wing root member and the main girder is directed from the root side to the tip side of the main girder. It is configured in a tapered shape that tapers. The rotational driving force from the rotor shaft is transmitted to the upper and lower outer skins and the main girder via the wing root member, and when the upper and lower outer skins forming the main outer shape of the main girder and the blade connected to it are rotated, the centrifugal force is generated. Although it will be applied to the wing root member, the centrifugal force is efficiently transmitted to the wing root member and the centrifugal force is transmitted to the wing root member because the joint between the wing root member and the main girder is configured in a tapered shape. Since the taper shape at the joint acts in the direction of tightening (in the direction in which the inner surface side taper shape part of the wing root member and the outer surface side taper shape part of the main girder bite into each other and tighten), the reliability of the joint at this joint part is increased. Will be improved. As a result, the necessary strength and rigidity required for the wing can be easily secured with a small number of constituent members, and the joints between the constituent members can be reliably and easily performed. In addition, the joining of the wing root member and the main girder can be achieved by directly joining the wing root member and the main girder without requiring a special additional member, and the target joining structure can be realized with a small number of constituent members. , It will also contribute to the weight reduction of the entire wing.

上記本発明に係る翼においては、上記主桁が中空構造に構成されていることが好ましい。中空構造の構成により、主桁の軽量化、ひいては翼全体の軽量化が可能になる。この中空構造は主桁の実質的に全長にわたっていることが好ましいが、軽量化の効果が大きい箇所を部分的に中空構造としてもよい。 In the blade according to the present invention, it is preferable that the main girder has a hollow structure. The hollow structure makes it possible to reduce the weight of the main girder and, by extension, the weight of the entire wing. It is preferable that this hollow structure extends over substantially the entire length of the main girder, but a portion where the effect of weight reduction is large may be partially hollowed.

上記主桁が中空構造に構成される場合、該主桁の板厚が、主桁根元側から先端側に向けて薄くなるように徐変している構成も好ましい。モーメント等の負荷の高い主桁根元側から相対的に負荷の低い先端側に向けて板厚を徐変させることにより、部位に応じた最適な板厚とすることができ、必要な強度を確保しながら軽量化の効果を発現できる。 When the main girder has a hollow structure, it is also preferable that the thickness of the main girder gradually changes from the root side to the tip side of the main girder. By gradually changing the plate thickness from the root side of the main girder, which has a high load such as moment, to the tip side, which has a relatively low load, the optimum plate thickness can be obtained according to the site, and the required strength is secured. However, the effect of weight reduction can be exhibited.

また、上記本発明に係る翼においては、上記主桁根元側に嵌入される蓋を有する構成とすることができる。主桁根元側に蓋が嵌入されることにより、少なくとも主桁の根元側における所定の形状が蓋によってより確実に維持され、その所定の形状の保持強度も蓋によってより確実に維持される。その結果、主桁全体をより確実に所定の形状に維持することが容易化され、翼の目標性能をより確実に確保できることになる。 Further, the wing according to the present invention may be configured to have a lid fitted to the base side of the main girder. By fitting the lid on the root side of the main girder, at least a predetermined shape on the root side of the main girder is more reliably maintained by the lid, and the holding strength of the predetermined shape is also more reliably maintained by the lid. As a result, it becomes easier to maintain the entire main girder in a predetermined shape more reliably, and the target performance of the blade can be more reliably secured.

上記蓋と主桁の接合部の形状は、特に限定されないが、テーパー形状に構成されていることが好ましい。テーパー形状に構成されていると、蓋が主桁根元側部分により確実に密着した状態で嵌入されることが可能になるので、上記のような蓋嵌入、接合による作用、効果をより確実に発現することが可能になる。 The shape of the joint portion between the lid and the main girder is not particularly limited, but it is preferably configured in a tapered shape. If the lid is configured in a tapered shape, the lid can be fitted in a state of being securely fitted to the base side portion of the main girder, so that the above-mentioned actions and effects of lid fitting and joining can be more reliably expressed. It will be possible to do.

また、本発明に係る翼においては、上記主桁の表面が、上記上下外皮の内面に沿う捩れ形状を有する構成とすることができる。翼の上下外皮は、翼の性能や効率の面から、しばしば捩れを有する複雑な曲面形状に形成されるが、主桁の表面も上下外皮の内面に沿う捩れ形状を有する構成とすることにより、上下外皮と主桁を確実にかつ容易に接合できる（例えば、接着により接合できる）ようになり、少ない構成部材点数でありながら、容易に望ましい翼の主要構造が構成される。 Further, in the wing according to the present invention, the surface of the main girder may have a twisted shape along the inner surfaces of the upper and lower outer skins. The upper and lower outer skins of the wing are often formed into a complicated curved surface shape with a twist from the viewpoint of the performance and efficiency of the wing. The upper and lower outer skins and the main girder can be joined reliably and easily (for example, they can be joined by adhesion), and the desired main structure of the wing is easily configured with a small number of constituent members.

また、本発明に係る翼においては、上記上下外皮の翼回転方向前後端に位置する前後端部材を有する構成とすることができる。これら前後端部材は、上下外皮の形状に沿う形状に形成されればよく、上下外皮に前後端部材を接続することにより、翼の外面の実質的に全体の形状が完成される。構成部材を上下外皮と前後端部材に分割しておくことで、製造の容易化が可能になる。 Further, the wing according to the present invention may have a front-rear end member located at the front-rear end in the wing rotation direction of the upper and lower outer skins. These front and rear end members may be formed in a shape that follows the shape of the upper and lower outer skins, and by connecting the front and rear end members to the upper and lower outer skins, substantially the entire shape of the outer surface of the wing is completed. By dividing the constituent members into upper and lower outer skins and front and rear end members, manufacturing can be facilitated.

また、本発明に係る翼においては、上記上下外皮の少なくとも一方と上記主桁との接合部が、接着接合によって、あるいは接着接合と凹凸の嵌め合いによって構成されている構造を採用できる。上下外皮の少なくとも一方と主桁とを接着により接合することによって、さらには接着接合と凹凸の嵌め合いにより接合することによって、両部材間に特別な部材を付加することなく、簡単な構造でかつ少ない構成部材点数で、外皮と主桁の望ましい接合が容易に達成される。 Further, in the wing according to the present invention, it is possible to adopt a structure in which at least one of the upper and lower outer skins and the main girder are joined by adhesive joining or by fitting the adhesive joint and unevenness. By joining at least one of the upper and lower outer skins and the main girder by adhesive, and by joining by adhesive joining and fitting of unevenness, it is possible to have a simple structure without adding a special member between both members. With a small number of components, the desired bond between the hull and the main girder is easily achieved.

さらに、本発明に係る翼においては、少なくとも上記主桁が繊維強化プラスチックからなることが好ましい。主桁に加え、上下外皮と翼根部材、さらには上記蓋も、繊維強化プラスチックからなる構成とすることができる。このように主要構成部材を繊維強化プラスチック製とすることにより、望ましい強度を確保しつつ、翼の軽量化をはかることができる。 Further, in the wing according to the present invention, it is preferable that at least the main girder is made of fiber reinforced plastic. In addition to the main girder, the upper and lower exodermis, the wing root member, and the lid may also be made of fiber reinforced plastic. By using fiber reinforced plastic as the main component in this way, it is possible to reduce the weight of the wing while ensuring the desired strength.

このように、本発明に係る翼によれば、少ない構成部材点数で確実に必要な連結や接合を行うことができ、捩じれ等の複雑な翼形状にも容易に対応できるようにした、とくに主要構成部材が繊維強化プラスチックからなり全体として軽量な、比較的大型の翼に適用して好適な、例えば比較的大型の風洞実験用設備等に好適な翼を提供することができる。 As described above, according to the wing according to the present invention, the necessary connection and joining can be reliably performed with a small number of constituent members, and complicated wing shapes such as twisting can be easily dealt with. It is possible to provide a wing suitable for application to a relatively large wing whose constituent member is made of fiber reinforced plastic and which is lightweight as a whole, for example, suitable for a relatively large wind tunnel experimental facility or the like.

本発明の一実施態様に係る翼の分解斜視図である。It is an exploded perspective view of the wing which concerns on one Embodiment of this invention. 図１の翼における繊維強化プラスチックからなる部分の板厚分布を示す部分斜視図である。It is a partial perspective view which shows the plate thickness distribution of the part made of fiber reinforced plastic in the wing of FIG.

以下に、本発明の実施の形態について、図面を参照しながら説明する。
図１は、本発明の一実施態様に係る翼を示しており、特に各主要構成部材が繊維強化プラスチックで構成された場合の一例を示している。図１において、１は翼全体を示しており、本実施態様では、翼１は、翼形状を形成する上外皮２および下外皮３と、ロータ軸（図示略）側に接続され上下外皮２、３が例えば連結部材（図示略）を介して連結される翼根部材４と、上下外皮２、３の内側に配設されて該上下外皮２、３に接合され翼根部材４を貫通して延びる主桁５と、上下外皮２、３の翼回転方向前後端に位置し上下外皮２、３に接続される前端部材６および後端部材７を有しており、主桁５の根元側には蓋８が嵌入されている。本実施態様では、これらの構成部材の全てが繊維強化プラスチックで構成されている。但し、少なくとも主桁５は繊維強化プラスチックで構成されていることが好ましいが、他の構成部材については繊維強化プラスチック以外の材質から構成することも可能である。繊維強化プラスチックの強化繊維としては、炭素繊維、ガラス繊維、アラミド繊維やこれら強化繊維の組合せを採用できる。 Hereinafter, embodiments of the present invention will be described with reference to the drawings.
FIG. 1 shows a wing according to an embodiment of the present invention, and shows an example in particular, when each main component is made of fiber reinforced plastic. In FIG. 1, 1 indicates the entire wing, and in the present embodiment, the wing 1 is connected to the upper outer skin 2 and the lower outer skin 3 forming the wing shape, and the upper and lower outer skins 2 connected to the rotor shaft (not shown) side. 3 is disposed inside the upper and lower outer skins 2 and 3 and is joined to the upper and lower outer skins 2 and 3 and penetrates the wing root member 4 which is connected to, for example, the wing root member 4 via a connecting member (not shown). It has an extending main girder 5, a front end member 6 and a rear end member 7 located at the front and rear ends of the upper and lower outer skins 2 and 3 in the wing rotation direction and connected to the upper and lower outer skins 2 and 3, and is located on the root side of the main girder 5. The lid 8 is fitted. In this embodiment, all of these components are made of fiber reinforced plastic. However, it is preferable that at least the main girder 5 is made of fiber reinforced plastic, but other constituent members may be made of a material other than fiber reinforced plastic. As the reinforcing fiber of the fiber reinforced plastic, carbon fiber, glass fiber, aramid fiber or a combination of these reinforcing fibers can be adopted.

上記翼根部材４と主桁５とは、互いに接合されており（例えば、接着により接合されており）、翼根部材４と主桁５との接合部では、該接合部が、つまり、翼根部材４の内面側部分および主桁５の外面側部分が、主桁５の根元側から先端側に向けて先細りとなるテーパー形状に構成されている。テーパー形状の構成により、遠心力が翼根部材４に加わる際にも遠心力が効率よく翼根部材４に伝達されるとともに、その遠心力が接合部におけるテーパー形状がより締まる方向に作用するので、この接合部における接合の確実性が向上される。したがって、この部分に関しては、少ない構成部材で翼に要求される必要な強度や剛性が容易に確保されつつ、構成部材間の接合が確実にかつ容易に行えるようになる。 The wing root member 4 and the main girder 5 are joined to each other (for example, they are joined by adhesion), and at the joint portion between the wing root member 4 and the main girder 5, the joint portion is, that is, the wing. The inner surface side portion of the root member 4 and the outer surface side portion of the main girder 5 are configured in a tapered shape that tapers from the root side to the tip end side of the main girder 5. Due to the tapered shape configuration, even when the centrifugal force is applied to the blade root member 4, the centrifugal force is efficiently transmitted to the blade root member 4, and the centrifugal force acts in the direction in which the tapered shape at the joint is tightened. , The reliability of the joint at this joint is improved. Therefore, with respect to this portion, the necessary strength and rigidity required for the wing can be easily secured with a small number of constituent members, and the joint between the constituent members can be reliably and easily performed.

また、本実施態様では、上記主桁５は、実質的に全長にわたって中空構造に（角型中空構造に）構成されており、主桁５の根元側は開口されている。この主桁根元側の開口部に上記蓋８が嵌入されており、この蓋８と主桁５との接合部もテーパー形状に構成されている。主桁５が中空構造に構成されることにより、主桁の軽量化、ひいては翼全体の軽量化が可能になる。主桁根元側に蓋８が嵌入されることにより、特に蓋８と主桁５との接合部もテーパー形状に構成されていることにより、少なくとも主桁５の根元側における所定の形状が蓋８によってより確実に維持され、その所定の形状の保持強度も蓋８によってより確実に維持される。したがって、主桁全体をより確実に所定の形状に維持することも容易化され、翼１の目標性能をより確実に確保できることになる。 Further, in the present embodiment, the main girder 5 is configured to have a hollow structure (in a square hollow structure) substantially over the entire length, and the root side of the main girder 5 is open. The lid 8 is fitted into the opening on the base side of the main girder, and the joint portion between the lid 8 and the main girder 5 is also configured to have a tapered shape. Since the main girder 5 has a hollow structure, the weight of the main girder can be reduced, and the weight of the entire wing can be reduced. By fitting the lid 8 on the root side of the main girder, in particular, the joint portion between the lid 8 and the main girder 5 is also configured to have a tapered shape, so that at least a predetermined shape on the root side of the main girder 5 is the lid 8. It is more reliably maintained by the lid 8, and the holding strength of the predetermined shape is also more reliably maintained by the lid 8. Therefore, it is easy to maintain the entire main girder in a predetermined shape more reliably, and the target performance of the blade 1 can be more reliably secured.

主桁５の形状は、それと接合される上下外皮２、３の形状に応じて適宜設計可能であり、特に上下外皮２、３が捩れ曲面形状を有する場合には、主桁５の表面が、上下外皮２、３の内面に沿う捩れ形状を有することが好ましい。これによって上下外皮２、３と主桁５との接合が、望ましい形態で強固に行われる。上下外皮２、３の少なくとも一方と主桁５との接合部は、接着接合によって構成されればよい。より強固な接合が望まれる場合には、接着接合と凹凸の嵌め合いによって構成されている構造を採用可能である。 The shape of the main girder 5 can be appropriately designed according to the shape of the upper and lower outer skins 2 and 3 to be joined to the main girder 5, and particularly when the upper and lower outer skins 2 and 3 have a twisted curved surface shape, the surface of the main girder 5 is formed. It is preferable to have a twisted shape along the inner surfaces of the upper and lower outer skins 2 and 3. As a result, the upper and lower outer skins 2 and 3 and the main girder 5 are firmly joined in a desirable form. The joint portion between at least one of the upper and lower outer skins 2 and 3 and the main girder 5 may be formed by adhesive joining. If a stronger bond is desired, a structure composed of an adhesive bond and an uneven fit can be adopted.

翼１の各部の板厚は、特に限定されず、翼１全体のサイズや強度や剛性の要求仕様に応じて適宜設計可能である。本実施態様のように前述の主要構成部材が繊維強化プラスチック、とくに炭素繊維強化プラスチックで構成される場合で、かつ、比較的大型の風洞実験用設備用の翼として作製される場合の板厚分布の例を図２に示す（板厚：ｔ［単位：ｍｍ］）。但し、図２に示す板厚分布は単に一例であって、翼の設計に際しては何らこれに拘束されない。 The plate thickness of each part of the blade 1 is not particularly limited, and can be appropriately designed according to the required specifications of the size, strength, and rigidity of the entire blade 1. Plate thickness distribution when the above-mentioned main components are made of fiber reinforced plastic, particularly carbon fiber reinforced plastic, as in the present embodiment, and when the blade is manufactured as a wing for a relatively large wind tunnel experimental facility. Is shown in FIG. 2 (plate thickness: t [unit: mm]). However, the plate thickness distribution shown in FIG. 2 is merely an example, and is not bound by this when designing the blade.

図２に示す板厚分布では、とくに中空構造の主桁５の板厚が、主桁根元側から先端側に向けて薄くなるように徐変している。前述したように、モーメント等の負荷の高い主桁根元側から相対的に負荷の低い先端側に向けて板厚を徐変させることにより、部位に応じた最適な板厚とすることができ、必要な強度を確保しながら一層の軽量化に貢献できる。 In the plate thickness distribution shown in FIG. 2, the plate thickness of the main girder 5 having a hollow structure is gradually changed so as to become thinner from the root side to the tip side of the main girder. As described above, by gradually changing the plate thickness from the root side of the main girder, which has a high load such as a moment, to the tip side, which has a relatively low load, the optimum plate thickness can be obtained according to the site. It can contribute to further weight reduction while ensuring the required strength.

また、各繊維強化プラスチックからなる各構成部材は、強化繊維層に関して積層構成を有することが好ましく、積層構成によって、より容易に望ましい機械特性を満たすことが可能になる。 Further, each component made of each fiber reinforced plastic preferably has a laminated structure with respect to the reinforced fiber layer, and the laminated structure makes it possible to more easily satisfy desired mechanical properties.

翼１の各構成部材における強化繊維層の積層構成の例を表１に示す。但し、表１に示す積層構成は単に一例であって、翼の設計に際しては何らこれに拘束されない。なお、表１に示す０°方向は、図２に示した方向である。 Table 1 shows an example of the laminated structure of the reinforcing fiber layer in each component of the blade 1. However, the laminated structure shown in Table 1 is merely an example, and is not bound by this when designing the blade. The 0 ° direction shown in Table 1 is the direction shown in FIG.

Figure 0007015151000001
Figure 0007015151000001

本発明に係る翼は、あらゆる分野の翼に適用可能であり、特に、比較的大型の翼、例えば比較的大型の風洞実験用設備等に好適なものである。 The wing according to the present invention can be applied to a wing in all fields, and is particularly suitable for a relatively large wing, for example, a relatively large wind tunnel experimental facility or the like.

１ 翼
２ 上外皮
３ 下外皮
４ 翼根部材
５ 主桁
６ 前端部材
７ 後端部材
８ 蓋 1 wing 2 upper outer skin 3 lower outer skin 4 wing root member 5 main girder 6 front end member 7 rear end member 8 lid

Claims (9)

回転駆動手段としてのロータ軸へと接続または連結される翼であって、翼形状を形成する上下外皮と、ロータ軸側に接続され前記上下外皮が連結される翼根部材と、前記上下外皮の内側に配設されて該上下外皮に接合され前記翼根部材を貫通して延びる主桁とを有し、前記翼根部材と前記主桁との接合部が、主桁について見た場合のロータ軸側の主桁根元側から先端側に向けて先細りとなるテーパー形状に構成されていることを特徴とする翼。 A wing connected to or connected to a rotor shaft as a rotation driving means, the upper and lower outer skins forming a blade shape, a wing root member connected to the rotor shaft side and to which the upper and lower outer skins are connected, and the upper and lower outer skins. It has a main girder that is arranged inside and is joined to the upper and lower outer skins and extends through the wing root member, and the joint portion between the wing root member and the main girder is a rotor when viewed with respect to the main girder. A wing characterized by being configured in a tapered shape that tapers from the root side of the main girder on the shaft side toward the tip side. 前記主桁が中空構造に構成されている、請求項１に記載の翼。 The wing according to claim 1, wherein the main girder has a hollow structure. 前記主桁の板厚が、主桁根元側から先端側に向けて薄くなるように徐変している、請求項２に記載の翼。 The wing according to claim 2, wherein the plate thickness of the main girder gradually changes from the root side to the tip side of the main girder. 前記主桁根元側に嵌入される蓋を有する、請求項１～３のいずれかに記載の翼。 The wing according to any one of claims 1 to 3, which has a lid fitted to the root side of the main girder. 前記蓋と前記主桁の接合部が、テーパー形状に構成されている、請求項４に記載の翼。 The wing according to claim 4, wherein the joint portion between the lid and the main girder is configured in a tapered shape. 前記主桁の表面が、前記上下外皮の内面に沿う捩れ形状を有する、請求項１～５のいずれかに記載の翼。 The wing according to any one of claims 1 to 5, wherein the surface of the main girder has a twisted shape along the inner surface of the upper and lower outer skins. 前記上下外皮の翼回転方向前後端に位置する前後端部材を有する、請求項１～６のいずれかに記載の翼。 The wing according to any one of claims 1 to 6, which has front and rear end members located at the front and rear ends in the wing rotation direction of the upper and lower outer skins. 前記上下外皮の少なくとも一方と前記主桁との接合部が、接着接合によって、あるいは接着接合と凹凸の嵌め合いによって構成されている、請求項１～７のいずれかに記載の翼。 The wing according to any one of claims 1 to 7, wherein the joint portion between at least one of the upper and lower outer skins and the main girder is formed by an adhesive joint or by an adhesive joint and an uneven fit. 少なくとも前記主桁が繊維強化プラスチックからなる、請求項１～８のいずれかに記載の翼。 The wing according to any one of claims 1 to 8, wherein at least the main girder is made of fiber reinforced plastic.
JP2017222663A 2017-11-20 2017-11-20 Wings Active JP7015151B2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP2017222663A JP7015151B2 (en) 2017-11-20 2017-11-20 Wings

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP2017222663A JP7015151B2 (en) 2017-11-20 2017-11-20 Wings

Publications (2)

Publication Number Publication Date
JP2019094796A JP2019094796A (en) 2019-06-20
JP7015151B2 true JP7015151B2 (en) 2022-02-02

Family

ID=66972737

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2017222663A Active JP7015151B2 (en) 2017-11-20 2017-11-20 Wings

Country Status (1)

Country Link
JP (1) JP7015151B2 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115163555B (en) * 2022-07-18 2024-02-13 江苏航宇航空装备制造有限公司 Carbon fiber blade used at low temperature

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2001165033A (en) 1999-12-10 2001-06-19 Tenryu Ind Co Ltd Propeller blade for wind power generator and method for manufacturing it, and main spar for propeller blade and method for manufacturing it
JP2002357176A (en) 2001-03-27 2002-12-13 Mitsubishi Heavy Ind Ltd Composite material blade for wind power generating device
JP2013194645A (en) 2012-03-21 2013-09-30 Mitsubishi Plastics Inc Blade for wind power generation apparatus

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2001165033A (en) 1999-12-10 2001-06-19 Tenryu Ind Co Ltd Propeller blade for wind power generator and method for manufacturing it, and main spar for propeller blade and method for manufacturing it
JP2002357176A (en) 2001-03-27 2002-12-13 Mitsubishi Heavy Ind Ltd Composite material blade for wind power generating device
JP2013194645A (en) 2012-03-21 2013-09-30 Mitsubishi Plastics Inc Blade for wind power generation apparatus

Also Published As

Publication number Publication date
JP2019094796A (en) 2019-06-20

Similar Documents

Publication Publication Date Title
JP6119044B2 (en) Composite beam chord material between reinforcing plates and associated manufacturing method
JP6628955B2 (en) Vertically integrated stringer
JP5308533B2 (en) Composite structure, aircraft main wing and aircraft fuselage provided with the same
JP6192285B2 (en) Root manufacturing
US8662847B2 (en) Rotor blade with control tube
US9822759B2 (en) Fixation for a wind turbine blade to the hub
US20100008789A1 (en) Reinforced blade for wind turbine
JPS6219639B2 (en)
US4793727A (en) Two-step composite joint
US9316203B2 (en) Blade connection for a rotor blade of a wind turbine
WO2012105415A1 (en) Composite material structure, and aircraft wing and fuselage provided therewith
CN107719628A (en) Rotor blade aircraft with the fuselage including at least one structural strengthening panel
BRPI0613658A2 (en) method for connecting at least two sheet-like formations, specifically at least two metal sheets to a lightweight structure, as well as lightweight connection
ES2955532T3 (en) Wind turbine blade spar structure and manufacturing method
CA1332054C (en) Integrated hub mast and rotorcraft rotor head comprising said hub mast
JP7015151B2 (en) Wings
CN105221357A (en) Wind turbine, wind turbine rotor blade, root of blade and root lining thereof
JP2017207001A (en) Wind turbine blade, wind turbine, process of manufacture for wind turbine blade and wind turbine blade connection structure
US4227859A (en) Rotor for a gyroplane
US4792280A (en) Helicopter rotor flexbeam
CN1298588C (en) Variable pitch rotor blade for shrouded rotors, in particular helicopter rotors
US11920556B2 (en) Wind turbine blade
JP6558185B2 (en) Girder structure
CN104071335B (en) The bar that compound matrix material is made
JP2010143484A (en) Method for determining cross section of flexible beam, and flexible beam

Legal Events

Date Code Title Description
A621 Written request for application examination

Free format text: JAPANESE INTERMEDIATE CODE: A621

Effective date: 20200923

A977 Report on retrieval

Free format text: JAPANESE INTERMEDIATE CODE: A971007

Effective date: 20210730

A131 Notification of reasons for refusal

Free format text: JAPANESE INTERMEDIATE CODE: A131

Effective date: 20210806

A521 Request for written amendment filed

Free format text: JAPANESE INTERMEDIATE CODE: A523

Effective date: 20210927

TRDD Decision of grant or rejection written
A01 Written decision to grant a patent or to grant a registration (utility model)

Free format text: JAPANESE INTERMEDIATE CODE: A01

Effective date: 20211224

A61 First payment of annual fees (during grant procedure)

Free format text: JAPANESE INTERMEDIATE CODE: A61

Effective date: 20220121