JP2008137445A - Leading edge structure of aircraft and manufacturing method thereof - Google Patents

Leading edge structure of aircraft and manufacturing method thereof Download PDF

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JP2008137445A
JP2008137445A JP2006324259A JP2006324259A JP2008137445A JP 2008137445 A JP2008137445 A JP 2008137445A JP 2006324259 A JP2006324259 A JP 2006324259A JP 2006324259 A JP2006324259 A JP 2006324259A JP 2008137445 A JP2008137445 A JP 2008137445A
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leading edge
front edge
composite material
reinforced composite
aircraft
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Iwao Maeda
巖 前田
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Shinmaywa Industries Ltd
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Shin Meiva Industry Ltd
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    • 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

Abstract

<P>PROBLEM TO BE SOLVED: To realize icing prevention and deicing in the leading edge of an aircraft without energy consumption. <P>SOLUTION: This manufacturing method comprises a process (P1) for impregnating at least a fiber in a fiber reinforced composite material with a water repellent material, a process (P2) for creating a laminate with the shape of the leading edge by laminating the fiber reinforced composite material sequentially and forming at least the outmost surface layer by using the fiber reinforced composite material impregnated with the water repellent material, and a process (P3) for hardening the laminate in the shape of the leading edge. <P>COPYRIGHT: (C)2008,JPO&INPIT

Description

本発明は、航空機の前縁構造及びそれの製造方法に関する。   The present invention relates to an aircraft leading edge structure and a method of manufacturing the same.

航空機の飛行中において、例えば主翼等の前縁部には過冷却水の衝突により氷が付着することがある。その付着した氷が成長した場合は、空気抵抗の増加や、揚力減少等を招くことから、その対策として、加熱空気式や電熱式等の防氷及び除氷装置を備えることが従来から知られている（例えば特許文献１，２参照）。
特開平９−７１２９８号公報 特開２００４−２５９２５号公報 During the flight of an aircraft, ice may adhere to the leading edge of, for example, the main wing due to the collision of supercooling water. When the adhering ice grows, it causes an increase in air resistance, a decrease in lift, etc., and as a countermeasure against this, it has hitherto been known to have a deicing and deicing device such as a heated air type or an electric heating type. (For example, refer to Patent Documents 1 and 2).
JP-A-9-71298 JP 2004-25925 A

しかしながら、例えば加熱空気式の防氷及び除氷装置は、エンジン抽気を利用することから燃費の悪化を招くと共に、例えば電熱式等の防氷及び除氷装置もまた、電力消費に伴い燃費の悪化を招くという問題があった。   However, for example, a heated air type anti-icing and deicing device uses engine bleed air, which causes a deterioration in fuel consumption. For example, an electric heating type anti-icing and deicing device also deteriorates in fuel consumption due to power consumption. There was a problem of inviting.

本発明は、かかる点に鑑みてなされたものであり、その目的とするところは、エネルギを消費することなく、航空機の前縁部における防氷及び除氷を実現することにある。   This invention is made | formed in view of this point, The place made into the objective is to implement | achieve deicing and deicing in the front edge part of an aircraft, without consuming energy.

本発明の一側面によると、航空機の前縁部を製造する方法は、繊維強化複合材料における少なくとも繊維に、撥水性材料を含浸する工程と、繊維強化複合材料を順次積層すると共に、少なくともその最表面の層を前記撥水性材料を含浸させた繊維強化複合材料によって形成することにより、前記前縁部の形状を有する積層体を作成する工程と、前記前縁部形状の積層体を硬化させる工程と、を含む。   According to one aspect of the present invention, there is provided a method for manufacturing a leading edge portion of an aircraft, wherein at least fibers in a fiber reinforced composite material are impregnated with a water repellent material, and a fiber reinforced composite material is sequentially laminated and Forming a laminate having the shape of the front edge by forming a surface layer of a fiber-reinforced composite material impregnated with the water repellent material; and curing the laminate having the shape of the front edge And including.

この構成によると、前縁部を構成する繊維強化複合材料における少なくとも繊維には、予め撥水性材料を含浸されており、そのため、その撥水性材料を含浸させた繊維強化複合材料を少なくとも最表面に積層させた積層体、ひいてはその積層体を硬化させて製造された前縁部は、その表面に撥水性を有することになる。   According to this configuration, at least the fibers in the fiber-reinforced composite material constituting the leading edge portion are impregnated with the water-repellent material in advance, so that the fiber-reinforced composite material impregnated with the water-repellent material is at least on the outermost surface. The laminated body, and thus the front edge portion produced by curing the laminated body, has water repellency on its surface.

それによって、その前縁部を有する航空機が飛行中に、過冷却水が前縁部におけるよどみ点に衝突しても氷の付着が抑制される。また、仮に氷が表面に付着してそれが多少成長したとても、その氷と表面との接着力は極めて弱いため、例えば翼の変位や気流の変化によってよどみ点の位置が変化することに伴い、氷は表面から容易に脱落する。尚、よどみ点以外の箇所においても、過冷却水はその表面に付着せずに後方に流れていくため、着氷は発生しない。   As a result, during the flight of the aircraft having the leading edge, even if supercooled water collides with the stagnation point at the leading edge, the adhesion of ice is suppressed. Also, if ice adheres to the surface and grows somewhat, the adhesive force between the ice and the surface is very weak, so for example, the position of the stagnation point changes due to the displacement of the wing or the change of airflow, Ice falls off the surface easily. In addition, in the places other than the stagnation point, the supercooled water flows backward without adhering to the surface, so that icing does not occur.

ここで、例えば撥水性材料を前縁部の表面にコーティングした場合は、そのコーティングの剥がれ等の問題が生じ得るが、本構成では繊維強化複合材の少なくとも繊維に撥水性材料を含浸させている、換言すれば、前縁部を構成する材料自体が撥水性を有しているため、そうした剥がれ等の問題が生じない。   Here, for example, when the surface of the front edge portion is coated with a water-repellent material, problems such as peeling of the coating may occur. However, in this configuration, at least the fibers of the fiber-reinforced composite material are impregnated with the water-repellent material. In other words, since the material constituting the front edge itself has water repellency, such a problem as peeling does not occur.

以上説明したように、本発明によると、前縁部を構成する繊維強化複合材料の少なくとも繊維に予め撥水性材料を含浸させ、その撥水性材料が含浸された繊維強化複合材料によって、前縁部の表面を構成することにより、その表面に撥水性を付与することができる。それによって、前縁部の防氷及び除氷を行うことができる。また、前縁部を構成する材料自体に撥水性を持たせているため、撥水性材料を前縁部にコーティングした場合に生じ得るコーティングの剥がれ等の問題を未然に回避することができる。   As described above, according to the present invention, at least the fiber of the fiber reinforced composite material constituting the front edge portion is impregnated with the water repellent material in advance, and the front edge portion is formed by the fiber reinforced composite material impregnated with the water repellent material. By constituting the surface, water repellency can be imparted to the surface. Thereby, deicing and deicing of the front edge can be performed. Further, since the material constituting the front edge itself has water repellency, problems such as peeling of the coating that may occur when the water repellent material is coated on the front edge can be avoided.

以下、本発明の実施形態を図面に基づいて説明する。尚、以下の好ましい実施形態の説明は、本質的に例示に過ぎず、本発明、その適用物或いはその用途を制限することを意図するものではない。   Hereinafter, embodiments of the present invention will be described with reference to the drawings. It should be noted that the following description of the preferred embodiment is merely illustrative in nature, and is not intended to limit the present invention, its application, or its use.

図１は、本発明に係る航空機の前縁構造が適用された主翼の前縁部分を示しており、この前縁部１は、例えばカーボン繊維強化複合材料によって形成されている。尚、図１では理解容易のために、複合材料の層の厚みを誇張して描いている。   FIG. 1 shows a leading edge portion of a main wing to which an aircraft leading edge structure according to the present invention is applied. The leading edge portion 1 is made of, for example, a carbon fiber reinforced composite material. In FIG. 1, the thickness of the composite material layer is exaggerated for easy understanding.

尚、前記主翼は、桁等を含めその全ての部位を繊維強化複合材料によって形成してもよいし、少なくとも前縁部１を繊維強化複合材料によって形成するのであれば、他の部位は繊維強化複合材料以外の材料、例えば金属材料等によって形成してもよい。また、主翼の翼型等については何ら制限がない。   The main wing may be formed of a fiber reinforced composite material in all parts thereof including a girder, etc., and at least the front edge portion 1 may be formed of a fiber reinforced composite material. You may form by materials other than a composite material, for example, a metal material etc. There are no restrictions on the wing shape of the main wing.

図２は、前記前縁部１の断面を拡大して示す図であり、この前縁部１は、樹脂材の内部に多数のカーボン繊維（例えばカーボンクロス等）３１，３２が積層されていると共に、カーボン繊維３１，３２はその層毎に所定の方向に配向されている。   FIG. 2 is an enlarged view showing a cross section of the front edge portion 1. The front edge portion 1 has a large number of carbon fibers (for example, carbon cloth) 31 and 32 laminated inside a resin material. At the same time, the carbon fibers 31 and 32 are oriented in a predetermined direction for each layer.

そして本実施形態においては特に、前記前縁部１の表面１１が撥水性を有しており、それによって、前縁部１への着氷や氷の成長が防止されるようになっている。   In the present embodiment, in particular, the surface 11 of the front edge portion 1 has water repellency, thereby preventing icing and ice growth on the front edge portion 1.

次に、前縁部１の製造方法について、図３を参照しながら説明する。先ず、複数のカーボン繊維を用意し、そのうちのいくつかについては、撥水性材料を含浸させる（図３のＰ１参照）。ここで、撥水性材料は特に限定されるものではないが、例えばフッ素化カーボン等とすることが可能である。   Next, the manufacturing method of the front edge part 1 is demonstrated, referring FIG. First, a plurality of carbon fibers are prepared, and some of them are impregnated with a water repellent material (see P1 in FIG. 3). Here, the water repellent material is not particularly limited, but may be, for example, fluorinated carbon.

次に、前縁部１の形状を有する所定の型に対して、例えばハンドレイアップ法等によって、カーボン繊維を順次積層していく（図３のＰ２参照）。そうして、前縁部１の形状を有する積層体を成形する。また、その積層体の少なくとも最表面の層は、前記撥水性材料を含浸させたカーボン繊維によって形成しておく。ここで、撥水性材料含浸のカーボン繊維の層としては、最表面の一層のみでもよいし、最表面の一層を含む複数の層としてもよい。尚、図２において、符号３１が撥水性材料含浸のカーボン繊維であり、符号３２が撥水性材料未含浸のカーボン繊維であり、撥水性材料含浸のカーボン繊維３１は、表面の２層を形成する。   Next, carbon fibers are sequentially laminated on a predetermined mold having the shape of the front edge 1 by, for example, a hand lay-up method (see P2 in FIG. 3). Thus, a laminate having the shape of the front edge 1 is formed. Further, at least the outermost layer of the laminate is formed by carbon fibers impregnated with the water repellent material. Here, the layer of the carbon fiber impregnated with the water repellent material may be only one layer on the outermost surface or a plurality of layers including one layer on the outermost surface. In FIG. 2, reference numeral 31 is a carbon fiber impregnated with a water repellent material, reference numeral 32 is a carbon fiber not impregnated with the water repellent material, and the carbon fiber 31 impregnated with the water repellent material forms two layers on the surface. .

そうして、樹脂未含浸の、前縁部１形状を有する積層体が完成すれば、それに樹脂を含浸させる。ここで、樹脂には撥水性材料を含有させておくことが望ましい。   Then, if a laminate having the shape of the leading edge 1 that is not impregnated with resin is completed, the laminate is impregnated with resin. Here, it is desirable that the resin contains a water repellent material.

このようにしてカーボン繊維強化複合材料により、前縁部１が成形されれば、その樹脂を硬化させることによって、前縁部１が完成する（図３のＰ３参照）。   Thus, if the front edge part 1 is shape | molded with a carbon fiber reinforced composite material, the front edge part 1 will be completed by hardening the resin (refer P3 of FIG. 3).

このようにして製造された前縁部１は、その少なくとも最表面が、撥水性材料含浸のカーボン繊維及び撥水性材料含有の樹脂によって形成されている。このため、前縁部１の表面１１は撥水性を有している。   At least the outermost surface of the front edge portion 1 manufactured in this way is formed of a carbon fiber impregnated with a water repellent material and a resin containing the water repellent material. For this reason, the surface 11 of the front edge part 1 has water repellency.

これによって、この主翼前縁部１を有する航空機が飛行している最中に、その前縁部１に過冷却水が衝突しても氷が付着することが抑制される。また、仮に氷が付着してそれが成長したとしても、氷と前縁部１の表面１１との接着力は極めて弱いため、主翼の変位や気流の変化によって氷は容易に剥がれる。そうして、防氷及び除氷効果が得られる。   As a result, during the flight of the aircraft having the main wing leading edge portion 1, it is possible to prevent ice from adhering to the leading edge portion 1 even if the supercooling water collides with the leading edge portion 1. Even if ice adheres and grows, the adhesive force between the ice and the surface 11 of the leading edge 1 is extremely weak, so that the ice is easily peeled off due to the displacement of the main wing and changes in the airflow. Thus, an anti-icing and de-icing effect is obtained.

またこの構成では、前縁部１の表面１１が撥水性を有していることによって防氷及び除氷効果が得られるため、例えばエンジン抽気の利用や電力の消費がなく、それによって燃費の悪化を抑制することができる。   Further, in this configuration, since the surface 11 of the front edge portion 1 has water repellency, an anti-icing and de-icing effect can be obtained. For example, there is no use of engine bleed or power consumption, thereby deteriorating fuel consumption. Can be suppressed.

さらにこの構成では、前縁部１を構成するための複合材料自体が撥水性を有しているため、例えば前縁部１の表面１１に撥水性材料をコーティングする場合とは異なり、そうしたコーティングが剥がれてしまうという問題がなく、航空機の前縁構造として適している。   Furthermore, in this configuration, since the composite material itself for forming the front edge portion 1 has water repellency, for example, unlike the case where the surface 11 of the front edge portion 1 is coated with a water repellent material, such coating is There is no problem of peeling off, and it is suitable as an aircraft leading edge structure.

尚、前記実施形態における繊維強化複合材料による前縁部１の成形は一例であり、公知の種々の方法を採用することが可能である。例えば、カーボン繊維に予め樹脂を含浸させてプリプレグとし、そのプリプレグを積層すると共に樹脂を硬化させることによって、前縁部１を製造してもよい。その場合も積層体の少なくとも最表面の層は、撥水性材料が含浸されたカーボン繊維及び樹脂を含むプリプレグによって形成すればよい。   In addition, shaping | molding of the front edge part 1 by the fiber reinforced composite material in the said embodiment is an example, and it is possible to employ | adopt various well-known methods. For example, the front edge portion 1 may be manufactured by impregnating a carbon fiber with a resin in advance to form a prepreg, laminating the prepreg and curing the resin. Even in that case, at least the outermost layer of the laminate may be formed of a prepreg containing carbon fibers impregnated with a water repellent material and a resin.

また、本発明は、主翼の前縁部１に適用することに限らず、航空機において従来より防氷乃至除氷システムが適用されている箇所に広く適用することが可能である。   In addition, the present invention is not limited to being applied to the leading edge 1 of the main wing, but can be widely applied to places where an anti-icing or de-icing system has been applied in an aircraft.

以上説明したように、本発明は、航空機の前縁部１の表面を撥水性を有する材料によって構成することにより、エネルギを消費することなく防氷及び除氷を行うことができるから、航空機の前縁構造及びそれの製造方法として有用である。   As described above, according to the present invention, since the surface of the front edge portion 1 of the aircraft is made of a material having water repellency, deicing and deicing can be performed without consuming energy. It is useful as a leading edge structure and a manufacturing method thereof.

主翼の前縁部１を示す断面図である。It is sectional drawing which shows the front edge part 1 of a main wing. 前縁部１の一部を拡大して示す拡大断面図である。It is an expanded sectional view which expands and shows a part of front edge part 1. FIG. 前縁部１の製造手順を示すフローチャートである。4 is a flowchart showing a manufacturing procedure of the front edge portion 1.

符号の説明Explanation of symbols

１ 前縁部
１１ 表面
３１，３２ カーボン繊維 1 Front edge 11 Surface 31, 32 Carbon fiber

Claims (2)

航空機の前縁部を製造する方法であって、
繊維強化複合材料における少なくとも繊維に、撥水性材料を含浸する工程と、
繊維強化複合材料を順次積層すると共に、少なくともその最表面の層を前記撥水性材料を含浸させた繊維強化複合材料によって形成することにより、前記前縁部の形状を有する積層体を作成する工程と、
前記前縁部形状の積層体を硬化させる工程と、を含む製造方法。 A method for manufacturing a leading edge of an aircraft, comprising:
Impregnating at least the fibers in the fiber reinforced composite material with a water repellent material;
A step of sequentially laminating the fiber reinforced composite material, and forming a laminate having the shape of the front edge by forming at least the outermost layer of the fiber reinforced composite material impregnated with the water repellent material; ,
Curing the laminate having the shape of the leading edge. 請求項１に記載の製造方法により製造された前縁部を含み、それによって、その表面が撥水性を有している航空機の前縁構造。   An aircraft leading edge structure comprising a leading edge portion manufactured by the manufacturing method according to claim 1, whereby the surface thereof has water repellency.
JP2006324259A 2006-11-30 2006-11-30 Leading edge structure of aircraft and manufacturing method thereof Pending JP2008137445A (en)

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KR102474962B1 (en) * 2021-08-13 2022-12-07 한국항공우주산업 주식회사 Method and system for manufacturing Composite material structures for ice protection

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JP2016028953A (en) * 2015-09-24 2016-03-03 富士重工業株式会社 Blade structure, aircraft blade, and wind turbine blade
KR102474962B1 (en) * 2021-08-13 2022-12-07 한국항공우주산업 주식회사 Method and system for manufacturing Composite material structures for ice protection

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