JPH05286496A - Wing structure - Google Patents
Wing structureInfo
- Publication number
- JPH05286496A JPH05286496A JP4114312A JP11431292A JPH05286496A JP H05286496 A JPH05286496 A JP H05286496A JP 4114312 A JP4114312 A JP 4114312A JP 11431292 A JP11431292 A JP 11431292A JP H05286496 A JPH05286496 A JP H05286496A
- Authority
- JP
- Japan
- Prior art keywords
- joint
- wing
- rib
- blade
- spars
- 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.)
- Withdrawn
Links
- 230000008878 coupling Effects 0.000 claims description 23
- 238000010168 coupling process Methods 0.000 claims description 23
- 238000005859 coupling reaction Methods 0.000 claims description 23
- 239000002131 composite material Substances 0.000 claims description 17
- 238000006243 chemical reaction Methods 0.000 abstract description 4
- 239000002184 metal Substances 0.000 abstract description 3
- 239000000463 material Substances 0.000 description 4
- 230000000694 effects Effects 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 239000004033 plastic Substances 0.000 description 2
- 229920003023 plastic Polymers 0.000 description 2
- 239000013585 weight reducing agent Substances 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 108010066278 cabin-4 Proteins 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 239000011162 core material Substances 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 239000003733 fiber-reinforced composite Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
- B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
- B29C65/5042—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like covering both elements to be joined
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/01—General aspects dealing with the joint area or with the area to be joined
- B29C66/05—Particular design of joint configurations
- B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
- B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
- B29C66/112—Single lapped joints
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/01—General aspects dealing with the joint area or with the area to be joined
- B29C66/05—Particular design of joint configurations
- B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
- B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
- B29C66/114—Single butt joints
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
- B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
- B29C66/52—Joining tubular articles, bars or profiled elements
- B29C66/524—Joining profiled elements
- B29C66/5244—Joining profiled elements for forming fork-shaped connections, e.g. for making window frames or Y-shaped pieces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
- B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
- B29C66/721—Fibre-reinforced materials
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
- B29C66/71—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the composition of the plastics material of the parts to be joined
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
- B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
- B29C66/721—Fibre-reinforced materials
- B29C66/7212—Fibre-reinforced materials characterised by the composition of the fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3085—Wings
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は、航空機の構造に関し、
複合材によりセミモノコック式とした翼構造に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an aircraft structure,
The present invention relates to a wing structure of a semi-monocoque type made of a composite material.
【０００２】[0002]
【従来の技術】従来、軽量で且つ強度が要求される航空
機の主翼等は、胴体から翼端に向けて延出する複数の翼
桁に所定間隔で複数のリブを結合して、その表面をパネ
ルで覆ったようなセミモノコック形式の翼構造がよく知
られている。そして金属製の場合であれば、翼桁の折曲
り部においてフランジ部同士を複数の金属継手を介し
て、リベット等で結合するような方式が一般的に採用さ
れる。一方、近年では、航空機の構造材料として例えば
各種プラスチック、繊維強化複合材等の複合材料が広く
採用されるようになっている。このような複合材は比強
度（強度／比重）、比弾性率（弾性率／比重）に優れて
いることから、航空機の機体構造部材として急速に普及
率が高まっている。2. Description of the Related Art Conventionally, a main wing or the like of an aircraft, which has been required to be lightweight and strong, has a plurality of ribs extending from a fuselage toward a wing tip to which a plurality of ribs are joined at predetermined intervals to form a surface thereof. A semi-monocoque wing structure that is covered with panels is well known. In the case of metal, a method is generally adopted in which the flange portions are joined to each other at the bent portion of the blade spar through a plurality of metal joints by rivets or the like. On the other hand, in recent years, composite materials such as various plastics and fiber reinforced composite materials have been widely adopted as structural materials for aircraft. Since such a composite material is excellent in specific strength (strength / specific gravity) and specific elastic modulus (elastic modulus / specific gravity), its prevalence rate is rapidly increasing as a structural member of an aircraft body.
【０００３】[0003]
【発明が解決しようとする課題】ところで、かかる翼の
構造は、通常、直線翼の場合であれば、モーメント荷
重、せん断荷重に対して有効に抵抗力を発揮すべく翼桁
とリブを結合して翼強度部材を構成しているが、例えば
翼の途中に折曲り部を設けて前進翼形態とし、このため
翼桁の折曲り部にねじり荷重を受けやすいような場合
で、しかも主要構造部材が複合材からなるような場合に
は、ねじり破壊防止のため特別の配慮が必要であった。
つまり、複合材の特性である材料の異方性を考慮し、最
も有効に耐ねじり剛性を高めることの出来る翼構造を採
用するとともに、複合材を使用する主目的である構造部
材の軽量化という効果を損わないように留意する必要が
あった。By the way, in the case of a straight blade, the structure of such a blade is usually formed by connecting the spars and ribs so as to effectively exert resistance to moment load and shear load. A wing strength member is constructed by using, for example, a bent portion is provided in the middle of the wing to form a forward wing shape, so that the bent portion of the spar is likely to receive a torsional load, and the main structural member If the is made of a composite material, special consideration was required to prevent torsional fracture.
In other words, considering the material anisotropy, which is a characteristic of the composite material, adopting a wing structure that can most effectively increase the torsional rigidity, and reducing the weight of the structural member, which is the main purpose of using the composite material. It was necessary to pay attention not to impair the effect.
【０００４】[0004]
【課題を解決するための手段】かかる課題を解決するた
め、本発明は複合材によるセミモノコック形式の翼構造
において、複数の翼桁と複数のリブの結合体からなる翼
強度部材と、この翼強度部材の周囲を覆う外皮部材を設
け、翼桁とリブのそれぞれに結合フランジ部を形成し
て、翼桁の結合フランジ部とリブの結合フランジ部同士
を継手部材で結合するようにした。そして各結合フラン
ジ部は、翼桁又はリブに一体成形で設けた。又、各結合
フランジ部には、継手部材を外表面に突出せしめないた
めの段付きを少なくとも継手部材の厚み分形成した。
又、翼桁とリブの結合構造は、翼桁の折曲り部に適用し
た。In order to solve the above problems, the present invention relates to a semi-monocoque type blade structure made of a composite material, and a blade strength member comprising a combination of a plurality of blade spars and a plurality of ribs, and this blade. An outer skin member that covers the periphery of the strength member is provided, a coupling flange portion is formed on each of the spars and the ribs, and the coupling flange portion of the spars and the coupling flange portions of the ribs are coupled by the coupling member. Each coupling flange portion is integrally formed with the spars or ribs. Further, each coupling flange portion is provided with a step for at least the thickness of the joint member so as not to project the joint member to the outer surface.
Further, the connecting structure of the spars and ribs was applied to the bent portion of the spars.
【０００５】[0005]
【作用】複合材で構成される翼桁とリブの結合フランジ
部同士を継手部材で結合することにより、より強固な剛
性の高いトルクボックスが形成出来る。更に特に大きな
ねじりモーメントの作用する翼桁の折曲り部に適用すれ
ば、ねじりモーメントによって翼桁に生ずる反力（いわ
ゆるキックロード）を有効にリブに伝達し荷重を分散さ
せることが出来る。この際、継手部材によって結合すれ
ば、各結合フランジ部の結合の信頼性が高まる。又、各
結合フランジ部を一体成形で形成することで、部品点数
の削減が可能となり、組み付け容易で且つ軽量化に寄与
する。又、結合フランジ部に段付きを設ければ、継手部
材が外表面に飛出さず、外皮部材との干渉が避けられ、
滑らかな外皮構造を確保出来る。By connecting the spar and the connecting flanges of the rib made of the composite material to each other with a joint member, a stronger and highly rigid torque box can be formed. Further, when it is applied to the bent portion of the spars which a particularly large torsion moment acts on, the reaction force (so-called kick load) generated in the spars due to the torsion moment can be effectively transmitted to the ribs to disperse the load. At this time, if the joint members are used for coupling, the reliability of coupling of the coupling flange portions is increased. Further, by forming each coupling flange portion by integral molding, it is possible to reduce the number of parts, which facilitates assembly and contributes to weight reduction. Further, if the connecting flange portion is provided with a step, the joint member does not project to the outer surface, and interference with the outer skin member is avoided,
A smooth skin structure can be secured.
【０００６】[0006]
【実施例】本発明の翼構造の実施例について添付した図
面に基づき説明する。図１は本発明の翼構造を主翼に適
用した航空機全体の分解斜視図、図２は主翼の構造を示
す平面図、図３は翼桁とリブの結合部まわりの拡大図で
あり、（Ａ）は結合前、（Ｂ）は結合状態、（Ｃ）は一
部を断面とした側面図である。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the wing structure of the present invention will be described with reference to the accompanying drawings. 1 is an exploded perspective view of an entire aircraft in which the wing structure of the present invention is applied to a main wing, FIG. 2 is a plan view showing the structure of the main wing, and FIG. 8B is a side view in which a part is a cross section, FIG.
【０００７】本発明の航空機は、機体全体の主要構造部
材が複合材で構成されており、例えば炭素繊維で強化し
たＣＦ／エポキシ樹脂のプラスチック系複合材等による
一次構造部材の周囲を同じく複合材の表皮で覆って軽量
化、小型化を図った航空機とされている。In the aircraft of the present invention, the main structural members of the entire fuselage are composed of a composite material. For example, a primary structural member made of a CF / epoxy resin plastic composite material or the like reinforced with carbon fibers is also surrounded by the composite material. It is said to be an aircraft that has been lightened and miniaturized by covering it with a skin.
【０００８】このため図１に示すように、例えば航空機
１の胴体２は、断面形状が略楕円形状の純モノコック構
造とし、適所に配置した複合材のフレームのまわりを複
合材の表皮（スキン）で覆うとともに、胴体の表皮の構
造は例えば芯材を複合材でサンドイッチ状にしたハニカ
ム構造としている。For this reason, as shown in FIG. 1, for example, the fuselage 2 of an aircraft 1 has a pure monocoque structure having a substantially elliptical cross-section, and the skin of the composite material is placed around the frame of the composite material arranged in place. In addition to being covered with, the structure of the skin of the body is, for example, a honeycomb structure in which a core material is sandwiched with a composite material.
【０００９】又、胴体２は前方からノーズ部３、キャビ
ン部４、アフト部５の３つのセクションの分割体からな
り、キャビン部４は乗員、乗客が搭乗する場所であって
与圧式キャビンとするとともに、アフト部５は貨物室と
して構成し、又、主翼６を取り付ける複数のメインフレ
ーム７、‥もアフト部５に設けている。Further, the body 2 is composed of a divided body of three sections including a nose portion 3, a cabin portion 4 and an aft portion 5 from the front. The cabin portion 4 is a place where passengers and passengers board and is a pressurized cabin. At the same time, the aft portion 5 is configured as a cargo room, and a plurality of main frames 7 to which the main wings 6 are attached are also provided in the aft portion 5.
【００１０】一方、主翼６は高翼で前進翼形態であり、
後述するように、複数の翼桁１２、１３とこの翼桁１
２、１３間に設けられた複数のリブ１５、１６を備え、
翼桁１２、１３の基端部が各メインフレーム７、‥の上
部に取り付けられて片持ち支持形式で支えられている。On the other hand, the main wing 6 is a high wing and has a forward wing form,
As will be described later, a plurality of wing spars 12, 13 and this wing spar 1
A plurality of ribs 15 and 16 provided between 2 and 13,
The base ends of the wing spar 12, 13 are attached to the upper portions of the main frames 7, ... And supported by a cantilever type.
【００１１】又、この左右の主翼６の上部で胴体２に近
接する箇所には、ターボファン式のエンジン８、８が一
対となって設けられており、又、不図示ではあるが胴体
内に収納自在とされた降着装置の主脚が、アフト部５の
メインフレーム７下方に取り付けられている。Further, a pair of turbofan type engines 8 and 8 are provided in the upper portions of the left and right main wings 6 in the vicinity of the fuselage 2, and although not shown, the turbofan type engines 8 and 8 are provided in the fuselage. The main leg of the landing gear that can be stored is attached below the main frame 7 of the aft portion 5.
【００１２】このため、この航空機１のキャビン部４
は、窓から通して得られる視界が主翼６、エンジン８等
によって遮られることがなく、又、高翼形態であるため
乗客、乗員等の乗降性が良く、更に、主翼取り付け部、
主脚取り付け部等の耐荷重構造の中心部がキャビン部４
を外れている等の点でキャビン室の快適性を重視して設
計された形態であるということが出来る。Therefore, the cabin portion 4 of the aircraft 1
The view obtained through the window is not blocked by the main wing 6, the engine 8 and the like, and because of the high wing form, passengers and passengers can get on and off easily.
The central part of the load-bearing structure such as the main landing gear mounting part is the cabin 4
It can be said that it is a form designed with emphasis on the comfort of the cabin room because it is out of the way.
【００１３】そして胴体２のアフト部５の後端には垂直
尾翼９が取り付けられ、更にその上部には水平尾翼１０
が取り付けられる。A vertical tail 9 is attached to the rear end of the aft portion 5 of the body 2, and a horizontal tail 10 is further provided above the vertical tail 9.
Is attached.
【００１４】それでは翼構造の細部について説明する。
図２に示すように、主翼６は胴体取り付け部から翼端に
亘って延出する前後２本の翼桁１２、１３と、これより
短い後桁１４を備え、前記２本の翼桁１２、１３の間に
は複数のリブ１５、１６、‥が結合されている。そし
て、これら翼桁１２、１３及びリブ１５、１６等の結合
体によって翼強度部材１１が構成され、この翼強度部材
１１の表面を外皮１９が覆っている。Now, details of the wing structure will be described.
As shown in FIG. 2, the main wing 6 includes two front and rear wing spars 12, 13 extending from the fuselage mounting portion to the wing tip, and a rear spar 14 shorter than the wing spar 12, and the two wing spars 12, A plurality of ribs 15, 16, ... Then, the blade strength member 11 is constituted by the combined body of the blade spars 12, 13 and the ribs 15, 16 and the like, and the outer skin 19 covers the surface of the blade strength member 11.
【００１５】又、２本の翼桁１２、１３は、胴体２への
結合側が機軸に対して略直角な基端部１２ａ、１３ａと
なり、折曲り部Ｋ（以下、キンク部という）を介して翼
端側が前方に折れ曲がって前進翼形態とされている。The two blade spars 12, 13 have base end portions 12a, 13a which are substantially perpendicular to the machine axis on the side of coupling to the body 2, and are bent via a bent portion K (hereinafter referred to as a kink portion). The wing tip side is bent forward to form a forward wing form.
【００１６】本発明は、かかる翼桁１２、１３のキンク
部Ｋのリブ１５の結合構造に特徴を有し、特に翼桁１
２、１３のキンク部Ｋに大きく作用するねじりモーメン
トの反力（キックロード）を有効にリブ１５に伝達し
て、各翼桁の基端部１２ａ、１３ａ、リブ１５及び胴体
２側のメインフレーム７等と一体となって、全体で曲げ
剛性及びねじり剛性を高めるようにしている。The present invention is characterized by the connecting structure of the ribs 15 of the kink portion K of the spars 12, 13 and particularly the spars 1
The reaction force (kick load) of the torsional moment that largely acts on the kink portion K of the blades 2 and 13 is effectively transmitted to the ribs 15, and the base end portions 12a and 13a of the respective spars, the ribs 15 and the main frame on the body 2 side. Together with 7 etc., the bending rigidity and the torsional rigidity are increased as a whole.
【００１７】ところで翼桁１２（翼桁１３も同様）は、
図３に示すように、縦向きのウェブ部１２ｗの上下端を
内方に折曲して断面コの字型の部材となっており、キン
ク部Ｋの上下の折曲げ端には、夫々結合フランジ部１２
ｆ、１２ｆを形成している。By the way, the wing spar 12 (as well as the wing spar 13) is
As shown in FIG. 3, upper and lower ends of the vertically oriented web portion 12w are bent inward to form a member having a U-shaped cross section, and the upper and lower bent ends of the kink portion K are connected to each other. Flange part 12
f and 12f are formed.
【００１８】一方、リブ１５側は、縦向きのウェブ部１
５ｗの上下から左右に張り出す張出部を備えて断面Ｉ型
に形成されるとともに、該張出部は長手方向の端部が広
く張り出して結合フランジ部１５ｆ、１５ｆとされてい
る。又、最先端部のウェブ部１５ｗ上下の張出部は所定
の長さ分が切り欠かれている。On the other hand, the rib 15 side is provided with the vertically oriented web portion 1
It is formed to have an I-shaped cross-section with an overhanging portion extending from the upper and lower sides of 5w to the left and right, and the overhanging portion is formed as a coupling flange portion 15f, 15f with the end portion in the longitudinal direction widely extending. In addition, the protruding portions above and below the frontmost web portion 15w are cut out by a predetermined length.
【００１９】そして、リブ１５先端のウェブ部１５ｗが
翼桁１２の上下の結合フランジ１２ｆ、１２ｆ間に差し
込まれて、ウェブ部１５ｗ先端面が翼桁１２のウェブ部
１２ｗに突き当たった際、両結合フランジ部１２ｆ、１
５ｆの先端面が僅かなクリアランスを持って対峙するよ
うにしている。尚、以上の翼桁１２の結合フランジ部１
２ｆとリブ１５の結合フランジ部１５ｆは、夫々翼桁１
２、リブ１５に一体成形されている。When the web portion 15w at the tip of the rib 15 is inserted between the upper and lower coupling flanges 12f and 12f of the blade spar 12, and when the tip end surface of the web portion 15w abuts on the web portion 12w of the blade spar 12, the two portions are joined. Flange 12f, 1
The tip surface of 5f faces each other with a slight clearance. In addition, the connecting flange portion 1 of the above spars 12
2f and the connecting flange portion 15f of the rib 15 are respectively provided on the spar 1
2. The rib 15 is integrally formed.
【００２０】又、結合フランジ部１２ｆ、１５ｆの先端
部には、段付きｍ、ｎが設けられている。この段付き
ｍ、ｎは以下に述べる表側継手部材１７を外表面に突出
せしめないためのものであり、上方の結合フランジ部１
２ｆ、１５ｆには、上部が凹部となる段差が、下方の結
合フランジ部１２ｆ、１５ｆには、下部が凹部となる段
差が形成されている。そしてこの段差は継手部材１７の
厚み以上としている。Steps m and n are provided at the tips of the coupling flanges 12f and 15f. The steps m and n are for preventing the front side joint member 17 described below from protruding to the outer surface, and the upper coupling flange portion 1
Steps 2f and 15f are formed with a concave portion in the upper portion, and step portions with a concave portion in the lower portion are formed on the lower coupling flange portions 12f and 15f. Further, this step difference is equal to or larger than the thickness of the joint member 17.
【００２１】継手部材１７、１８は図３（Ｃ）に示すよ
うに、両結合フランジ部１２ｆ、１５ｆのフランジ面の
表裏面に添い当てて結合するため表側継手部材１７と裏
側継手部材１８からなり、プレート状をなしている。そ
して、裏側継手部材１８はウェブ部１５ｗを挟んで両側
の結合フランジ部１２ｆ、１５ｆの裏面を止め付けるべ
く幅の狭い一対の部材から構成されている。そして、既
述のように表側継手部材１７で結合しても外表面に突出
しないため、その上を外皮部材１９で覆っても表面に段
差が形成されず滑らかとなる。尚、各ウェブ部１２ｗ、
１５ｗ同士はＬ字金具２０でも結合するようにしてい
る。As shown in FIG. 3 (C), the joint members 17 and 18 are composed of a front joint member 17 and a back joint member 18 so that they are joined by abutting on the front and back surfaces of the flange surfaces of both joint flange portions 12f and 15f. , Plate-shaped. The back joint member 18 is composed of a pair of narrow members for holding the back surfaces of the coupling flange portions 12f and 15f on both sides with the web portion 15w interposed therebetween. Further, as described above, even if they are joined by the front joint member 17, they do not project to the outer surface, so even if they are covered with the outer skin member 19, no step is formed on the surface and the surface becomes smooth. In addition, each web part 12w,
The 15w parts are also joined together by the L-shaped fitting 20.
【００２２】以上のような結合構造の作用について述べ
る。図２に示すようなキンク部Ｋを有する前進翼形態の
主翼６には、ねじりモーメントの影響が大きく作用す
る。つまりキンク部Ｋを有する翼桁１２、１３の場合は
直線翼では発生しないねじりモーメントが該キンク部Ｋ
に集中するからである。The operation of the above-described bond structure will be described. The effect of the torsional moment is great on the main wing 6 in the form of a forward wing having the kink portion K as shown in FIG. That is, in the case of the girders 12 and 13 having the kink portion K, the twisting moment that does not occur in the straight blade is the kink portion K.
Because it concentrates on.
【００２３】そしてこのねじり力によって翼桁１２、１
３に生ずる反力は、継手部材１７、１８を介してリブ１
５に伝達され、荷重を分散させることによってねじり剛
性を高めている。Then, due to this torsional force, the wing spar 12, 1
3 is applied to the rib 1 via the joint members 17 and 18.
5, the torsional rigidity is increased by distributing the load.
【００２４】この際、両結合フランジ部１２ｆ、１５ｆ
の張り出し方向、及び継手部材１７、１８の結合は、ね
じりモーメントによって生ずる荷重を最も有効に伝達し
得る構造であり、荷重の方向に対して面内で支えること
が出来るものである。このことは特に複合材が面外荷重
に対して弱いという点から重要なポイントである。At this time, both coupling flange portions 12f, 15f
The overhang direction and the coupling of the joint members 17 and 18 are structures that can most effectively transfer the load generated by the torsion moment, and can support the load in the plane in the direction of the load. This is an important point especially since the composite material is weak against the out-of-plane load.
【００２５】尚、実施例では翼桁１２、１３のキンク部
Ｋに適用するようにしているが、かかる箇所に限られる
ことがないのはいうまでもない。Although the embodiment is applied to the kink portion K of the blade spars 12 and 13, it goes without saying that the invention is not limited to such a portion.
【００２６】[0026]
【発明の効果】以上のように本発明の翼構造は複合材を
構造部材としたセミモノコック式の翼構造において、翼
桁に生ずるねじり反力を継手部材によって最も有効にリ
ブに伝達するようにしたため、翼桁に加わる荷重が有効
に分散され、ねじり剛性が高まる。この際、結合フラン
ジ部を一体成形しているため部品点数が削減され、組み
付け容易且つ軽量化に寄与する。又、結合フランジ部の
段付きによって継手部材が突出せず、外表面を滑らかに
仕上げることが出来る。As described above, in the blade structure of the present invention, in the semi-monocoque type blade structure using the composite material as a structural member, the torsional reaction force generated in the spar is transmitted to the rib most effectively by the joint member. Therefore, the load applied to the spars is effectively dispersed, and the torsional rigidity is increased. At this time, since the coupling flange portion is integrally molded, the number of parts is reduced, which contributes to easy assembly and weight reduction. Further, the joint member does not project due to the stepped joint flange portion, and the outer surface can be finished smoothly.
【図１】本発明の翼構造を主翼に適用した航空機全体の
分解斜視図FIG. 1 is an exploded perspective view of an entire aircraft in which a wing structure of the present invention is applied to a main wing.
【図２】主翼の構造を示す平面図FIG. 2 is a plan view showing the structure of a main wing.
【図３】翼桁とリブの結合部まわりの拡大図であり、
（Ａ）は結合前、（Ｂ）は結合状態、（Ｃ）は一部を断
面とした側面図FIG. 3 is an enlarged view around a connecting portion between a spar and a rib,
(A) is a side view before joining, (B) is a joined state, (C) is a partial cross-sectional view
【符号の説明】 １ 航空機 ２ 胴体 ６ 主翼 １１ 翼強度部材 １２、１３ 翼桁 １２ｆ 結合フランジ部 １２ｗ ウェブ部 １５、１６ リブ １５ｆ 結合フランジ部 １５ｗ ウェブ部 ｍ、ｎ 段付き １７、１８ 継手部材 １９ 外皮部材 Ｋ 折曲り部[Explanation of symbols] 1 aircraft 2 fuselage 6 main wing 11 wing strength member 12, 13 blade spar 12f coupling flange portion 12w web portion 15, 16 rib 15f coupling flange portion 15w web portion m, n stepped 17, 18 joint member 19 outer skin Material K Bent part
Claims (4)
造において、この翼は、複数の翼桁と複数のリブの結合
体からなる翼強度部材と、この翼強度部材の周囲を覆う
外皮部材を有するとともに、前記翼桁とリブはそれぞれ
ウェブ部と結合フランジ部を備え、該翼桁の結合フラン
ジ部とリブの結合フランジ部同士を継手部材で結合する
ようにしたことを特徴とする翼構造。1. A semi-monocoque type wing structure made of a composite material, wherein the wing has a blade strength member composed of a combination of a plurality of blade spars and a plurality of ribs, and a skin member covering the periphery of the blade strength member. In addition, the blade spar and the rib each include a web portion and a connecting flange portion, and the connecting flange portion of the blade spar and the connecting flange portion of the rib are connected by a joint member.
又はリブに一体成形されることを特徴とする翼構造。2. The wing structure, wherein each of the coupling flange portions is integrally formed with a spar or rib.
記継手部材との重合部に該継手部材の厚み以上の段付き
を形成したことを特徴とする請求項１に記載の翼構造。3. The blade structure according to claim 1, wherein a stepped portion having a thickness equal to or larger than a thickness of the joint member is formed at a portion where each joint flange portion overlaps with the joint member.
曲り部に適用したことを特徴とする請求項１又は請求項
２に記載の翼構造。4. The blade structure according to claim 1, wherein the connecting structure of the spars and the ribs is applied to a bent portion of the spars.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4114312A JPH05286496A (en) | 1992-04-08 | 1992-04-08 | Wing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4114312A JPH05286496A (en) | 1992-04-08 | 1992-04-08 | Wing structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH05286496A true JPH05286496A (en) | 1993-11-02 |
Family
ID=14634713
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP4114312A Withdrawn JPH05286496A (en) | 1992-04-08 | 1992-04-08 | Wing structure |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH05286496A (en) |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1996039326A1 (en) * | 1995-06-06 | 1996-12-12 | The Boeing Company | Resistance welding of thermoplastics in aerospace structure |
| WO2006100400A1 (en) * | 2005-03-23 | 2006-09-28 | Airbus France | Device and method for non-symmetrical mixed carbon-metal assembly |
| WO2008032040A1 (en) * | 2006-09-12 | 2008-03-20 | Gkn Aerospace Services Limited | Rib post |
| JP2009519175A (en) * | 2005-12-16 | 2009-05-14 | エアバス・ユ―ケ―・リミテッド | Assembly of aircraft parts |
| WO2010061020A1 (en) * | 2008-11-27 | 2010-06-03 | Airbus Operations, S.L. | Front trimming fitting and related assembly |
| JP2011502886A (en) * | 2007-11-20 | 2011-01-27 | エアバス・オペレーションズ・ゲーエムベーハー | Coupling device for coupling fuselage sections, coupling of the coupling device to at least one fuselage section and method for manufacturing the coupling device |
| ES2394579A1 (en) * | 2010-03-29 | 2013-02-01 | Airbus Operations S.L. | System of coupling of aircraft components (Machine-translation by Google Translate, not legally binding) |
| WO2015032276A1 (en) * | 2013-09-03 | 2015-03-12 | 中国商用飞机有限责任公司 | Fuselage butt joint structure connected to aircraft vertical fin, and aircraft comprising fuselage butt joint structure |
| RU2613551C1 (en) * | 2015-12-10 | 2017-03-17 | Публичное акционерное общество "Научно-производственная корпорация "Иркут" | Aircraft wing mounting device |
| JP2017529276A (en) * | 2014-09-29 | 2017-10-05 | ザ・ボーイング・カンパニーＴｈｅ Ｂｏｅｉｎｇ Ｃｏｍｐａｎｙ | Spar with kick for rudder and elevator applications |
| CN107416183A (en) * | 2016-09-06 | 2017-12-01 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of spar attachment structure of aircraft wing |
| US10407152B2 (en) * | 2015-12-07 | 2019-09-10 | Bell Helicopter Textron Inc. | Fuselage to wing attachment |
| EP4151521A1 (en) * | 2021-09-15 | 2023-03-22 | Airbus Urban Mobility GmbH | An aircraft with a forward-swept wing in shoulder-wing configuration |
-
1992
- 1992-04-08 JP JP4114312A patent/JPH05286496A/en not_active Withdrawn
Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1996039326A1 (en) * | 1995-06-06 | 1996-12-12 | The Boeing Company | Resistance welding of thermoplastics in aerospace structure |
| WO2006100400A1 (en) * | 2005-03-23 | 2006-09-28 | Airbus France | Device and method for non-symmetrical mixed carbon-metal assembly |
| FR2883548A1 (en) * | 2005-03-23 | 2006-09-29 | Airbus France Sas | DEVICE AND METHOD FOR DISSYMMETRIC CARBON-METAL MIXED DISCHARGE |
| JP2008534347A (en) * | 2005-03-23 | 2008-08-28 | エアバス・フランス | Asymmetric carbon metal mixed seam joining apparatus and method |
| JP2009519175A (en) * | 2005-12-16 | 2009-05-14 | エアバス・ユ―ケ―・リミテッド | Assembly of aircraft parts |
| WO2008032040A1 (en) * | 2006-09-12 | 2008-03-20 | Gkn Aerospace Services Limited | Rib post |
| JP2010502516A (en) * | 2006-09-12 | 2010-01-28 | ジーケイエヌ エアロスペース サービシイズ リミテッド | Rib post |
| US8393575B2 (en) | 2006-09-12 | 2013-03-12 | Gkn Aerospace Services Limited | Rib post |
| JP2011502886A (en) * | 2007-11-20 | 2011-01-27 | エアバス・オペレーションズ・ゲーエムベーハー | Coupling device for coupling fuselage sections, coupling of the coupling device to at least one fuselage section and method for manufacturing the coupling device |
| CN102300772A (en) * | 2008-11-27 | 2011-12-28 | 空中客车西班牙运营有限责任公司 | Front Trimming Fitting And Related Assembly |
| ES2364109A1 (en) * | 2008-11-27 | 2011-08-25 | Airbus Operations, S.L. | Front trimming fitting and related assembly |
| US8186621B2 (en) | 2008-11-27 | 2012-05-29 | Airbus Operations S.L. | Assembly between a front fitting and the traction coupling of the two lateral boxes of the horizontal stabilizer of an aircraft |
| WO2010061020A1 (en) * | 2008-11-27 | 2010-06-03 | Airbus Operations, S.L. | Front trimming fitting and related assembly |
| ES2394579A1 (en) * | 2010-03-29 | 2013-02-01 | Airbus Operations S.L. | System of coupling of aircraft components (Machine-translation by Google Translate, not legally binding) |
| WO2015032276A1 (en) * | 2013-09-03 | 2015-03-12 | 中国商用飞机有限责任公司 | Fuselage butt joint structure connected to aircraft vertical fin, and aircraft comprising fuselage butt joint structure |
| JP2017529276A (en) * | 2014-09-29 | 2017-10-05 | ザ・ボーイング・カンパニーＴｈｅ Ｂｏｅｉｎｇ Ｃｏｍｐａｎｙ | Spar with kick for rudder and elevator applications |
| US10364015B2 (en) | 2014-09-29 | 2019-07-30 | The Boeing Company | Kicked spars for rudder and elevator applications |
| US10647405B2 (en) | 2014-09-29 | 2020-05-12 | The Boeing Company | Kicked spars for rudder and elevator applications |
| US10407152B2 (en) * | 2015-12-07 | 2019-09-10 | Bell Helicopter Textron Inc. | Fuselage to wing attachment |
| RU2613551C1 (en) * | 2015-12-10 | 2017-03-17 | Публичное акционерное общество "Научно-производственная корпорация "Иркут" | Aircraft wing mounting device |
| CN107416183A (en) * | 2016-09-06 | 2017-12-01 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of spar attachment structure of aircraft wing |
| CN107416183B (en) * | 2016-09-06 | 2024-01-09 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Spar connection structure of aircraft wing |
| EP4151521A1 (en) * | 2021-09-15 | 2023-03-22 | Airbus Urban Mobility GmbH | An aircraft with a forward-swept wing in shoulder-wing configuration |
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