JP2008114707A - Main wing structure of aircraft - Google Patents

Main wing structure of aircraft Download PDF

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JP2008114707A
JP2008114707A JP2006299469A JP2006299469A JP2008114707A JP 2008114707 A JP2008114707 A JP 2008114707A JP 2006299469 A JP2006299469 A JP 2006299469A JP 2006299469 A JP2006299469 A JP 2006299469A JP 2008114707 A JP2008114707 A JP 2008114707A
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spar
fuselage
main
main wings
wings
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JP4657191B2 (en
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Kazuhide Hasegawa
一英 長谷川
Atsushi Nakazawa
淳 中澤
Hirohide Azuma
弘英 東
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Honda Motor Co Ltd
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Honda Motor Co Ltd
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Abstract

<P>PROBLEM TO BE SOLVED: To provide a main wing structure of an aircraft reduced in the number of component items and the assembly man-hours by simplifying a structure of coupling parts of right and left main wings of the aircraft. <P>SOLUTION: Curved parts 23, 24, 25 curved along a lower portion of a fuselage are integrated with a main spar 13, a front spar 14 and a rear spar 15 of right and left main wings 12L, 12R, respectively. Inner ends in the right-to-left direction of the right and left curved parts 23, 24, 25 are butted to each other on the center line of the aircraft body, and coupled to each other via connection fittings 26, etc., and connection plates 27, etc. The number of components and the man-hour of the coupling works can be reduced in comparison with a case in which the main spar 13, the front spar 14 and the rear spar 15 of the right and left main wings 12L, 12R are connected via a carry-through. In addition, by forming the curved parts 23, 24, 25, any interference of the right and left main wings 12L, 12R with the fuselage is avoided, and an internal space of the fuselage is effectively used. <P>COPYRIGHT: (C)2008,JPO&INPIT

Description

本発明は、左右の主翼を胴体の下部において結合する飛行機の主翼構造に関する。   The present invention relates to an aircraft main wing structure in which left and right main wings are joined at the lower part of a fuselage.

一般に、低翼の飛行機の左右の主翼は別々に組み立てられて一体に結合された後に、胴体の下部に取り付けられる。この場合、円形断面の胴体の下部に沿うように湾曲した湾曲部と、この湾曲部の左右両端から左右方向に延びる一対の連結部とを一体に形成したキャリースルーを用い、キャリースルーの左右の連結部に左右の主翼の内端を連結して一体に組み立てた後に、前記キャリースルーを胴体の下部に取り付けるものが、下記特許文献１や下記特許文献２により公知である。
特開２００３−２０５８９９号公報 特表２００３−５３３４０６号公報 Generally, the left and right main wings of a low wing airplane are assembled separately and joined together, and then attached to the lower part of the fuselage. In this case, a carry-through that integrally forms a curved portion that is curved along the lower portion of the trunk having a circular cross section and a pair of connecting portions that extend in the left-right direction from the left and right ends of the curved portion is used. It is known from Patent Document 1 and Patent Document 2 below that the carry-through is attached to the lower part of the fuselage after the inner ends of the left and right main wings are connected to the connecting portion and assembled integrally.
JP 2003-205899 A Special table 2003-533406 gazette

しかしながら、キャリースルーを用いて左右の主翼を胴体に取り付けるものでは、左右の主翼以外にキャリースルーの分だけ部品点数が増加するだけでなく、キャリースルーと左右の主翼との結合部分が２か所になるため、結合作業の工数が増加して生産性が低下する問題があった。   However, if the left and right main wings are attached to the fuselage using carry-through, not only the left and right main wings, but also the number of parts is increased by the amount of carry-through, and there are two joints between the carry-through and the left and right main wings. Therefore, there has been a problem that the man-hour for the joining work increases and the productivity decreases.

本発明は前述の事情に鑑みてなされたもので、飛行機の左右の主翼の結合部の構造を簡素化して部品点数および組付工数を削減することを目的とする。   The present invention has been made in view of the above-described circumstances, and an object thereof is to simplify the structure of the connecting portion between the left and right main wings of an airplane to reduce the number of parts and the number of assembling steps.

上記目的を達成するために、請求項１に記載された発明によれば、左右の主翼を胴体の下部において結合する飛行機の主翼構造において、左右の主翼のスパーに胴体の下部に沿って湾曲する湾曲部を一体に形成し、左右の湾曲部の左右方向内端を機体中心線上で突き合わせて連結フィッティングを介して結合したことを特徴とする飛行機の主翼構造が提案される。   In order to achieve the above object, according to the first aspect of the present invention, in the main wing structure of an airplane in which the left and right main wings are joined at the lower part of the fuselage, the left and right main wing spar curves along the lower part of the fuselage. A main wing structure for an airplane is proposed in which curved portions are integrally formed, inner ends in the left-right direction of the left and right curved portions are butted on the fuselage center line, and are connected via a coupling fitting.

また請求項２に記載された発明によれば、請求項１の構成に加えて、左右の主翼のスパーにそれぞれ支持される複数のリブのうち、左右方向内端に位置する二つのリブは前記連結フィッティングの左右方向外端よりも外側に配置され、前記二つのリブの間で左右の主翼の下面を覆うロアスキンに機体中心線を跨ぐアクセスホールを形成したことを特徴とする飛行機の主翼構造が提案される。   According to the invention described in claim 2, in addition to the configuration of claim 1, of the plurality of ribs respectively supported by the spar of the left and right main wings, An aircraft main wing structure characterized in that an access hole is formed on the lower skin that is disposed outside the left and right outer ends of the coupling fitting and covers the lower surface of the left and right main wings between the two ribs and straddles the fuselage center line. Proposed.

尚、実施の形態のメインスパー１３、フロントスパー１４およびリヤスパー１５は本発明のスパーに対応する。   The main spar 13, the front spar 14, and the rear spar 15 of the embodiment correspond to the spar of the present invention.

請求項１の構成によれば、左右の主翼のスパーに胴体の下部に沿って湾曲する湾曲部を一体に形成し、左右の湾曲部の左右方向内端を機体中心線上で突き合わせて連結フィッティングを介して結合したので、左右の主翼のスパーをキャリースルーを介して連結する場合に比べて、部品点数および結合作業の工数を削減することができる。しかもスパーに湾曲部を形成したことで、左右の主翼が胴体と干渉することを回避し、胴体の内部空間を有効に利用することができる。   According to the configuration of the first aspect, the curved portions that are curved along the lower portion of the fuselage are integrally formed in the spar of the left and right main wings, and the right and left inner ends of the left and right curved portions are abutted on the fuselage center line to perform connection fitting. Therefore, the number of parts and the number of man-hours for joining work can be reduced as compared with the case where the spar of the left and right main wings is connected via a carry-through. In addition, since the curved portion is formed in the spar, the left and right main wings can be prevented from interfering with the fuselage, and the internal space of the fuselage can be used effectively.

また請求項２の構成によれば、左右の主翼のリブのうち左右方向内端に位置する二つのリブを連結フィッティングの左右方向外端よりも外側に配置し、前記二つのリブの間で左右の主翼の下面を覆うロアスキンに機体中心線を跨ぐアクセスホールを形成したので、そのアクセスホールの面積を充分に大きく確保することができ、アクセスホールを通して左右の主翼のスパーの湾曲部を連結フィッティングを介して連結する際の作業性を高めることができる。   According to the second aspect of the present invention, the two ribs positioned at the inner end in the left-right direction among the ribs of the left and right main wings are disposed outside the outer end in the left-right direction of the coupling fitting, and the right and left between the two ribs An access hole that spans the fuselage centerline is formed in the lower skin that covers the lower surface of the main wing, so that the area of the access hole can be secured sufficiently large, and the curved fitting of the spar of the left and right main wings can be connected through the access hole. Workability at the time of connecting via can be improved.

以下、本発明の実施の形態を添付の図面に基づいて説明する。   Embodiments of the present invention will be described below with reference to the accompanying drawings.

図１〜図６は本発明の実施の形態を示すもので、図１は飛行機の全体斜視図、図２は図１の２方向拡大矢視図、図３は図２の３方向矢視図、図４は図３の４−４線断面図、図５は図３の５−５線断面図、図６は連結フィッティングおよび連結板の斜視図である。   1 to 6 show an embodiment of the present invention. FIG. 1 is an overall perspective view of an airplane, FIG. 2 is an enlarged view in two directions in FIG. 1, and FIG. 3 is an arrow in three directions in FIG. 4 is a sectional view taken along line 4-4 of FIG. 3, FIG. 5 is a sectional view taken along line 5-5 of FIG. 3, and FIG. 6 is a perspective view of a coupling fitting and a coupling plate.

図１および図２に示すように、低翼の飛行機の胴体１１の下部に支持された左右の主翼１２Ｌ，１２Ｒは、概ねスパン方向に延びるメインスパー１３と、メインスパー１３の前方に配置されたフロントスパー１４と、メインスパー１３の後方に配置されたリヤスパー１５とを備える。メインスパー１３、フロントスパー１４およびリヤスパー１５はコード方向に延びる多数のリブ１６…で接続されており、メインスパー１３、フロントスパー１４およびリヤスパー１５およびリブ１６…の上面および下面はそれぞれアッパースキン１７およびロアスキン１８で覆われる。フロントスパー１４の前部には前縁スキン１９が結合され、左右の主翼１２Ｌ，１２Ｒの後縁部のスパン方向内側にフラップ２０，２０が揺動自在に支持され、フラップ２０，２０のスパン方向外側にエルロン２１，２１が揺動自在に支持される。   As shown in FIGS. 1 and 2, the left and right main wings 12 </ b> L and 12 </ b> R supported on the lower part of the fuselage 11 of the low wing airplane are disposed in front of the main spar 13 and the main spar 13 extending in the span direction. A front spar 14 and a rear spar 15 disposed behind the main spar 13 are provided. The main spar 13, the front spar 14, and the rear spar 15 are connected by a large number of ribs 16 extending in the cord direction. The upper and lower surfaces of the main spar 13, the front spar 14, the rear spar 15, and the ribs 16 are respectively an upper skin 17 and an upper skin 17. Covered with lower skin 18. A front edge skin 19 is coupled to the front portion of the front spar 14, and flaps 20, 20 are swingably supported on the inner sides of the rear edges of the left and right main wings 12 </ b> L, 12 </ b> R. Ailerons 21 and 21 are swingably supported on the outside.

左右の主翼１２Ｌ，１２Ｒのメインスパー１３、フロントスパー１４およびリヤスパー１５は基本的に直線状の部材であるが、その内端部つまり胴体１１の下部に取り付けられる部分には、下方に円弧状に湾曲した湾曲部２３，２４，２５が形成される。湾曲部２３，２４，２５は円形断面の胴体１１の下面に沿う形状を有しており、左右の主翼１２Ｌ，１２Ｒを胴体１１に取り付ける部分で、湾曲部２３，２４，２５が胴体１１と干渉しないようになっている。   The main spar 13, the front spar 14 and the rear spar 15 of the left and right main wings 12L and 12R are basically linear members. Curved curved portions 23, 24, and 25 are formed. The curved portions 23, 24, and 25 have a shape along the lower surface of the fuselage 11 having a circular cross section. The curved portions 23, 24, and 25 interfere with the fuselage 11 at the portions where the left and right main wings 12 </ b> L and 12 </ b> R are attached to the fuselage 11. It is supposed not to.

左右の主翼１２Ｌ，１２Ｒのメインスパー１３、フロントスパー１４およびリヤスパー１５の湾曲部２３，２４，２５は、機体中心線Ｌ上でそれぞれ２個の連結フィッティン２６，２６および１個の連結板２７を介して一体に連結される。メインスパー１３、フロントスパー１４およびリヤスパー１５の連結部の構造は実質的に同一であるため、その代表としてリヤスパー１５の連結部の構造を図２〜図６に基づいて説明する。   The main spar 13 of the left and right main wings 12L and 12R, the curved portions 23, 24, and 25 of the front spar 14 and the rear spar 15 have two connecting fittings 26 and 26 and one connecting plate 27 on the body center line L, respectively. Are connected together. Since the structure of the connecting portion of the main spar 13, the front spar 14, and the rear spar 15 is substantially the same, the structure of the connecting portion of the rear spar 15 will be described based on FIGS.

湾曲部２５を含むリヤスパー１５は、基本的にウエブ２８および上下のフランジ２９，３０を有するＩ型断面を有しており、ウエブ２８には複数の薄肉部２８ａ…が形成され、隣接する薄肉部２８ａ…間にウエブ２８および上下のフランジ２９，３０を連結する補強壁３１…が形成され、ウエブ２８およびフランジ２９，３０にはそれぞれファスナ孔２８ｂ…，２９ａ…，３０ａ…が形成される（図５参照）。   The rear spar 15 including the curved portion 25 basically has an I-shaped cross section having a web 28 and upper and lower flanges 29, 30. The web 28 is formed with a plurality of thin portions 28a. Reinforcing walls 31 for connecting the web 28 and the upper and lower flanges 29, 30 are formed between 28a ..., and fastener holes 28b ..., 29a ..., 30a ... are formed in the web 28 and the flanges 29, 30 respectively (see FIG. 5).

連結フィッティング２６はＨ型の部材であって、上下のフランジ当接部２６ａ，２６ｂと、それらの左右方向中央部を上下に連結する連結壁２６ｃと、上下のフランジ当接部２６ａ，２６ｂおよび連結壁２６ｃに沿ってＵ字状に形成された左右のウエブ当接部２６ｄ，２６ｄとを備える。フランジ当接部２６ａ，２６ｂには複数のファスナ孔２６ｅ…が所定間隔で形成され、ウエブ当接部２６ｄ，２６ｄには複数のファスナ孔２６ｆ…が所定間隔で形成される（図５および図６参照）。連結板２７は僅かに湾曲した矩形状の板材であり、そこにファスナ孔２７ａ…が２列に形成される（図６参照）。   The coupling fitting 26 is an H-shaped member, and includes upper and lower flange abutting portions 26a and 26b, a coupling wall 26c that vertically couples the center portions in the left and right direction, upper and lower flange abutting portions 26a and 26b, and a coupling. Left and right web contact portions 26d, 26d formed in a U shape along the wall 26c. A plurality of fastener holes 26e are formed at predetermined intervals in the flange contact portions 26a and 26b, and a plurality of fastener holes 26f are formed at predetermined intervals in the web contact portions 26d and 26d (FIGS. 5 and 6). reference). The connecting plate 27 is a slightly curved rectangular plate material, in which fastener holes 27a are formed in two rows (see FIG. 6).

しかして、左右のリヤスパー１５，１５の湾曲部２５，２５の内端どうしを突き合わせ、その前後面に２個の連結フィッティング２６，２６を位置決めすると、各連結フィッティング２６は、上側のフランジ当接部２６ａが左右のリヤスパー１５，１５の湾曲部２５，２５の上側のフランジ２９の下面に当接し、下側のフランジ当接部２６ｂが左右のリヤスパー１５，１５の湾曲部２５，２５の下側のフランジ３０の上面に当接し、左右のウエブ当接部２６ｄ，２６ｄが湾曲部２５，２５のウエブ２８に当接する。   When the inner ends of the curved portions 25, 25 of the left and right rear spars 15, 15 are brought into contact with each other and the two coupling fittings 26, 26 are positioned on the front and rear surfaces thereof, each coupling fitting 26 is connected to the upper flange contact portion. 26a is in contact with the lower surface of the upper flange 29 of the curved portions 25, 25 of the left and right rear spars 15, 15, and the lower flange contact portion 26b is on the lower side of the curved portions 25, 25 of the left and right rear spars 15, 15. The left and right web contact portions 26d and 26d contact the upper surface of the flange 30 and the web 28 of the curved portions 25 and 25.

この状態で、アッパースキン１７と、連結板２７と、左右の湾曲部２５，２５の上側のフランジ２９，２９と、連結フィッティング２６の上側のフランジ当接部２６ａとが、それらを貫通するファスナ３２で締結され、ロアスキン１８と、左右の湾曲部２５，２５の下側のフランジ３０，３０と、連結フィッティング２６の下側のフランジ当接部２６ｂとが、それらを貫通するファスナ３３で締結される。更に、二つの連結フィッティング２６，２６のウエブ当接部２６ｄ，２６ｄと、それらに挟まれた湾曲部２５，２５のウエブ２８，２８とが、それらを貫通するファスナ３４で締結される。   In this state, the upper skin 17, the connecting plate 27, the upper flanges 29 and 29 of the left and right curved portions 25 and 25, and the upper flange contact portion 26a of the connecting fitting 26 pass through the fastener 32. The lower skin 18, the lower flanges 30, 30 of the left and right curved portions 25, 25, and the lower flange contact portion 26 b of the coupling fitting 26 are fastened by a fastener 33 that passes through them. . Further, the web contact portions 26d, 26d of the two coupling fittings 26, 26 and the webs 28, 28 of the curved portions 25, 25 sandwiched between them are fastened by fasteners 34 penetrating them.

図２から明らかなように、機体中心線Ｌ上で３対の連結フィッティング２６…を用いて連結された左右の主翼１２Ｌ，１２Ｒのメインスパー１３、フロントスパー１４およびリヤスパー１５の湾曲部２３，２４，２５には、それらを連結する連結フィッティング２６…の左右両端の近傍を通過してコード方向に延びる左右一対の最内端のリブ１６Ｉ，１６Ｉが固定される。メインスパー１３、フロントスパー１４およびリヤスパー１５の下面を覆うロアスキン１８には、左右一対の最内端のリブ１６Ｉ，１６Ｉに挟まれた位置に、機体中心線Ｌを跨ぐ３個のアクセスホール１８ａ…が形成される。前側の１個のアクセスホール１８ａはメインスパー１３およびフロントスパー１４間に設けられ、後側の２個のアクセスホール１８ａ，１８ａはメインスパー１３およびリヤスパー１５間に設けられる。これらのアクセスホール１８ａ…は着脱自在なアクセスパネル３５…により開閉される。   As is clear from FIG. 2, the curved portions 23 and 24 of the main spar 13, the front spar 14 and the rear spar 15 of the left and right main wings 12L and 12R connected on the airframe center line L using three pairs of coupling fittings 26. 25, a pair of left and right innermost ribs 16I, 16I extending in the cord direction passing through the vicinity of the left and right ends of the coupling fittings 26,. The lower skin 18 that covers the lower surfaces of the main spar 13, the front spar 14 and the rear spar 15 has three access holes 18 a that straddle the fuselage center line L at a position sandwiched between a pair of left and right innermost ribs 16 I and 16 I. Is formed. One front access hole 18 a is provided between the main spar 13 and the front spar 14, and the two rear access holes 18 a and 18 a are provided between the main spar 13 and the rear spar 15. These access holes 18a are opened and closed by a detachable access panel 35.

前記アクセスホール１８ａ…はメインスパー１３、フロントスパー１４およびリヤスパー１５の湾曲部２３，２４，２５を連結フィッティング２６…および連結板２７…で連結する作業を行うとき、その作業用の開口として利用される。このとき、機体中心線Ｌ上、つまりメインスパー１３、フロントスパー１４およびリヤスパー１５の湾曲部２３，２４，２５の結合部上にはリブが配置されていないため、機体中心線Ｌを跨ぐように形成された大型のアクセスホール１８ａ…がリブによって分割されることがなくなり、アクセスホール１８ａ…の使い勝手が良好になる。   The access hole 18a is used as an opening for connecting the curved portions 23, 24, and 25 of the main spar 13, the front spar 14, and the rear spar 15 with the connection fittings 26 and the connection plates 27. The At this time, no ribs are arranged on the fuselage centerline L, that is, on the joints of the curved portions 23, 24, and 25 of the main spar 13, the front spar 14, and the rear spar 15, so The large access holes 18a formed are not divided by the ribs, and the usability of the access holes 18a is improved.

以上のように、左右の主翼１２Ｌ，１２Ｒのメインスパー１３、フロントスパー１４およびリヤスパー１５に胴体１１の下部に沿って湾曲する湾曲部２３，２４，２５を一体に形成し、左右の湾曲部２３，２４，２５の左右方向内端を機体中心線Ｌ上で突き合わせて連結フィッティング２６…を介して結合したので、左右の主翼１２Ｌ，１２Ｒのメインスパー１３、フロントスパー１４およびリヤスパー１５をキャリースルーを介して連結する場合に比べて、部品点数および結合作業の工数を削減することができる。またメインスパー１３、フロントスパー１４およびリヤスパー１５に湾曲部２３，２４，２５を形成したことで、左右の主翼１２Ｌ，１２Ｒが胴体１１と干渉することを回避し、胴体１１の内部空間を有効に利用することができる。   As described above, the curved portions 23, 24, and 25 that are curved along the lower portion of the fuselage 11 are integrally formed on the main spar 13, the front spar 14, and the rear spar 15 of the left and right main wings 12L and 12R. , 24, 25 and the inner ends of the left and right direction are abutted on the fuselage center line L and connected via the coupling fittings 26, so that the main spar 13, the front spar 14 and the rear spar 15 of the left and right main wings 12L, 12R are carried through. The number of parts and the number of man-hours for coupling work can be reduced as compared with the case of connecting via the connection. Further, the curved portions 23, 24, 25 are formed in the main spar 13, the front spar 14, and the rear spar 15, so that the left and right main wings 12L, 12R are prevented from interfering with the fuselage 11, and the internal space of the fuselage 11 is made effective. Can be used.

以上、本発明の実施の形態を説明したが、本発明はその要旨を逸脱しない範囲で種々の設計変更を行うことが可能である。   The embodiments of the present invention have been described above, but various design changes can be made without departing from the scope of the present invention.

例えば、実施の形態では主翼１２Ｌ，１２Ｒがメインスパー１３、フロントスパー１４およびリヤスパー１５の３本のスパーを備えているが、スパーの数は３本に限定されるものではない。   For example, in the embodiment, the main wings 12L and 12R include the three spars of the main spar 13, the front spar 14, and the rear spar 15, but the number of spar is not limited to three.

また連結フィッティング２６の形状は実施の形態に限定されず、連結板２７は場合によって廃止することができる。   The shape of the coupling fitting 26 is not limited to the embodiment, and the coupling plate 27 can be eliminated depending on circumstances.

飛行機の全体斜視図Overall perspective view of airplane 図１の２方向拡大矢視図2 direction enlarged view of FIG. 図２の３方向矢視図3 direction arrow view of FIG. 図３の４−４線断面図Sectional view taken along line 4-4 in FIG. 図３の５−５線断面図Sectional view along line 5-5 in FIG. 連結フィッティングおよび連結板の斜視図Perspective view of coupling fitting and coupling plate

符号の説明Explanation of symbols

１１ 胴体
１２Ｌ 主翼
１２Ｒ 主翼
１３ メインスパー（スパー）
１４ フロントスパー（スパー）
１５ リヤスパー（スパー）
１６ リブ
１６Ｉ 左右方向内端に位置する二つのリブ
１８ ロアスキン
１８ａ アクセスホール
２３ 湾曲部
２４ 湾曲部
２５ 湾曲部
２６ 連結フィッティング
Ｌ 機体中心線 11 fuselage 12L main wing 12R main wing 13 main spar (spar)
14 Front spar
15 Rear spar (spar)
16 Ribs 16I Two ribs 18 located at the inner end in the left-right direction 18 Lower skin 18a Access hole 23 Bending portion 24 Bending portion 25 Bending portion 26 Connecting fitting L Machine body center line

Claims (2)

左右の主翼（１２Ｌ，１２Ｒ）を胴体（１１）の下部において結合する飛行機の主翼構造において、
左右の主翼（１２Ｌ，１２Ｒ）のスパー（１３，１４，１５）に胴体（１１）の下部に沿って湾曲する湾曲部（２３，２４，２５）を一体に形成し、左右の湾曲部（２３，２４，２５）の左右方向内端を機体中心線（Ｌ）上で突き合わせて連結フィッティング（２６）を介して結合したことを特徴とする飛行機の主翼構造。 In the aircraft main wing structure in which the left and right main wings (12L, 12R) are joined at the bottom of the fuselage (11),
The spar (13, 14, 15) of the left and right main wings (12L, 12R) is integrally formed with curved portions (23, 24, 25) that are curved along the lower portion of the fuselage (11), and the left and right curved portions (23 , 24, 25) a main wing structure of an airplane characterized in that the inner ends in the left-right direction are butted on the fuselage center line (L) and connected via a coupling fitting (26). 左右の主翼（１２Ｌ，１２Ｒ）のスパー（１３，１４，１５）にそれぞれ支持される複数のリブ（１６）のうち、左右方向内端に位置する二つのリブ（１６Ｉ）は前記連結フィッティング（２６）の左右方向外端よりも外側に配置され、前記二つのリブ（１６Ｉ）の間で左右の主翼（１２Ｌ，１２Ｒ）の下面を覆うロアスキン（１８）に機体中心線（Ｌ）を跨ぐアクセスホール（１８ａ）を形成したことを特徴とする、請求項１に記載の飛行機の主翼構造。   Of the plurality of ribs (16) respectively supported by the spar (13, 14, 15) of the left and right main wings (12L, 12R), the two ribs (16I) positioned at the inner ends in the left-right direction are the coupling fitting (26 ) On the outer side of the outer edge in the left and right direction, and an access hole straddling the fuselage center line (L) on the lower skin (18) between the two ribs (16I) and covering the lower surfaces of the left and right main wings (12L, 12R) The main wing structure of an airplane according to claim 1, wherein (18a) is formed.
JP2006299469A 2006-11-02 2006-11-02 Aircraft main wing structure Active JP4657191B2 (en)

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JP2010503571A (en) * 2006-09-15 2010-02-04 エアバス ドイッチュラント ゲゼルシャフト ミット ベシュレンクテル ハフツング Aerodynamic member, carrier wing with aerodynamic member, computer with motion drive control module, computer program, aerodynamic assembly, and method of affecting secondary turbulence
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EP3674204A1 (en) * 2018-12-26 2020-07-01 Airbus Operations SAS Aircraft wing unit comprising two wings attached to one another
EP3998192A1 (en) * 2021-02-19 2022-05-18 Lilium eAircraft GmbH Wing spar structure

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CN106218861B (en) * 2016-09-06 2018-10-16 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 aircraft wing

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JP2010503571A (en) * 2006-09-15 2010-02-04 エアバス ドイッチュラント ゲゼルシャフト ミット ベシュレンクテル ハフツング Aerodynamic member, carrier wing with aerodynamic member, computer with motion drive control module, computer program, aerodynamic assembly, and method of affecting secondary turbulence
WO2018203191A1 (en) * 2017-05-01 2018-11-08 Bombardier Inc. Aircraft wing unit with upper wing skin defining pressure floor
CN110582444A (en) * 2017-05-01 2019-12-17 庞巴迪公司 Aircraft wing unit with upper wing skin defining pressure floor
CN110582444B (en) * 2017-05-01 2023-03-07 庞巴迪公司 Aircraft wing unit with upper wing skin defining pressure floor
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EP3674204A1 (en) * 2018-12-26 2020-07-01 Airbus Operations SAS Aircraft wing unit comprising two wings attached to one another
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EP3998192A1 (en) * 2021-02-19 2022-05-18 Lilium eAircraft GmbH Wing spar structure

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