JP2006315642A - Vertical taking-off/landing machine "win rotor" (wing rotary) - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide an aircraft with a simple structure and inexpensive body production cost in a vertical taking off/landing type aircraft capable of being driven by force of small horsepower and landing at any place. <P>SOLUTION: A shaft is mounted to a front part of a wing and it is fixed to a drive device such as a chain or the like provided at both sides (or a central part) to make a rotary wing. A large number of rotary wings are installed with a distance gap that they are not overlapped and track walls having a bearing or the like for supporting the drive device in the rotatable state and supporting the wing at a rear part of the rotary wing are mounted to both sides (or a central part) of a flying object. A device capable of driving the chain or the like is separately installed at an appropriate position and when the chain is driven, lift by wind force is generated by rotating the respective rotary wings. The aircraft capable of approximately vertically taking off/landing can be provided. <P>COPYRIGHT: (C)2007,JPO&INPIT

Description

発明の詳細な説明Detailed Description of the Invention

本発明は滑走路を必要としない垂直離着陸機に関し、特に、上部軌道壁を飛行本体と上下に分離した軌道において、多数の平行回転する翼の回転動作により発生する風力の作用によって揚力を得る垂直離着陸自在機に関するものである。  The present invention relates to a vertical take-off and landing aircraft that does not require a runway, and in particular, in a trajectory in which an upper trajectory wall is separated from a flying body vertically, a vertical force is obtained by the action of wind force generated by the rotational motion of a number of parallel rotating wings. It relates to take-off and landing aircraft.

現在利用されている飛行機は長い滑走路を有する飛行場でないと利用できない為、飛行場は広大な面積を必要としている。又ジェットエンジン等の騒音問題も生じている。一方、垂直離着陸できる乗物としてはヘリコプターがあるが、大きなプロペラ回転翼を必要とするために、エンジンの騒音、翼端の超音速振動や砂塵巻き上げ問題が生じている。  Airplanes currently in use can only be used on airfields with long runways, so the airfield requires a vast area. There is also a noise problem with jet engines. On the other hand, there is a helicopter as a vehicle capable of vertical takeoff and landing. However, since a large propeller rotor blade is required, engine noise, supersonic vibration of the blade tip, and dust hoisting have occurred.

ヘリコプターの円回転翼では軸の中心付近では低速の為揚力は発生せず、末端付近では超音速スピードになり、揚力は回転翼半径の約１／３でしか発生していない。そのうえ、前傾姿勢で前進している時は円運動の半分の後退翼は前進、揚力発生を妨害している。本発明は平行移動回転翼のため、ヘリの翼半径の約１／３付近の面風速以下の回転で、有効揚力発生面積は数倍も大きいので最大の揚力を発生させる事が可能です。  In the helicopter's circular rotor blades, lift is not generated near the center of the shaft because of the low speed, supersonic speed is generated near the end, and lift force is generated only about 1/3 of the rotor blade radius. In addition, when moving forward in a forward leaning posture, half of the retreating wings of the circular motion block forward and lift generation. Since the present invention is a parallel-moving rotor blade, the maximum lift force can be generated because the effective lift force generation area is several times larger when the surface wind speed is about 1/3 of the helicopter blade radius.

仏国特許第８６７４４２号明細書には、多数の翼を組み合わせ、翼を平行回転する航空機に関する発明が開示されている。（特許文献１） 同様な方法は国際特許公開ＷＯ７９／００９４５号公報にも示されている。（特許文献２）
しかしながら、ここで開示されている方法は軌道や個々の軸を固定し一定角度により揚力を発生する方法で、且つ戦車のキャタピラーの固定した構造に類似している。
各々の回転翼が自由な角度に設定できて最適な揚力を発生させる本発明とは違う方法である。公開特許は多数の翼から構成された物を飛行機主翼の上部一部や機体側面に設置したりするタイプのもので、回転時に得られる揚力の大きさに限度があり、本発明の回転翼は飛行物体の全体を覆い、最大の面積で揚力を発揮するこの形式とは全く異なる。
ＦＲ第８６７４４２号公報 ＷＯ７９／００９４５号公報 French Patent No. 867442 discloses an invention relating to an aircraft in which multiple wings are combined and the wings rotate in parallel. (Patent Document 1) A similar method is also disclosed in International Patent Publication WO79 / 00945. (Patent Document 2)
However, the method disclosed here is a method of generating lift at a fixed angle by fixing a track and individual shafts, and is similar to a fixed structure of a tank caterpillar.
This is a method different from the present invention in which each rotor blade can be set at a free angle to generate an optimum lift. The open patent is a type in which an object composed of a large number of wings is installed on the upper part of the airplane main wing or on the side of the fuselage, and there is a limit to the amount of lift that can be obtained during rotation. It is completely different from this type that covers the whole flying object and exerts lift in the largest area.
FR 867442 WO79 / 00945 Publication

発明が解決しようとする課題Problems to be solved by the invention

長い滑走路を必要とせず、しかも大きな騒音の発生しない垂直離着陸自在な航空機を提供し、尚、本体構造が単純で、躯体製作費用も安価で、大きな格納庫も必要としない垂直離着陸可能な航空機を提供することを課題とする。
地上、水上（雪上、砂漠）空中等を活躍の場所に出来る為、滑走路建設の困難な離島間交通や近距離自家用機としての利用。山林消火、農薬散布等には後退翼軌道外側水密部のその下にタンクを設置すれば風波が立っていても水面を滑走の必要が無く、安全に作業が出来る。又、雪山遭難時には転落した人の横斜面に軟着陸して機内に側近から収容出来き、人命救助が迅速に解決出来る。Providing a vertical take-off and landing aircraft that does not require a long runway and that does not generate significant noise, and that has a simple body structure, low cost for building a housing, and does not require a large hangar. The issue is to provide.
Because it can be used as an active place on the ground, on the water (snow, desert), etc., it can be used as a remote island traffic and difficult-to-use aircraft for difficult runway construction. For fire extinguishing in forests, spraying agricultural chemicals, etc., if a tank is installed under the watertight part outside the swept wing orbit, there is no need to glide on the surface of the water even if a wind wave is standing, and work can be done safely. Also, in the event of a snowy mountain disaster, it can softly land on the side slope of a fallen person and can be accommodated in the aircraft from the side, and lifesaving can be solved quickly.

課題を解決するための手段Means for solving the problem

翼の前部に主軸を取り付け、両サイド（又は中央）に設けたチェーン等の駆動装置に固定し、回転翼とする。このような回転翼をお互いが重なり合うことがない距離間隔で多数設置し、該駆動装置を駆動可能な状態で支え、且つ回転翼の後部部分にて翼を支えるベアリング、タイヤ等の副軸又は中央軸等を通過させる軌道壁を飛行物体の両側（又は中央）に取り付ける。
最大の揚力を確保する為に上部軌道壁を飛行本体と上下に分離し、且つ回転翼は飛行物体の全体を覆い、最大の面積で揚力を発揮するようにした。
チェーン等を駆動できる装置を別途適当な位置に設置し、チェーンを駆動した場合に、それぞれの回転翼が回転をすることによって、風力による揚力を発生する。この事により機体加重より大きな揚力に達した時に浮上し、機体加重と揚力がバランスした場合には空中に停止し、機体加重が揚力より大きい場合は下降するという原理に基づいて、ほぼ垂直に離着陸可能な航空機を提供できる事を見い出した。A main shaft is attached to the front part of the blade and fixed to a driving device such as a chain provided on both sides (or the center) to form a rotating blade. A large number of such rotor blades are installed at a distance interval where they do not overlap each other, the drive device is supported in a drivable state, and the rear shaft of the rotor blade supports the blade at the rear part of the rotor, the countershaft or the center of the tire, etc. A track wall that passes the shaft or the like is attached to both sides (or the center) of the flying object.
In order to ensure maximum lift, the upper track wall was separated from the flying body vertically, and the rotating wings covered the entire flying object so as to exert lift in the maximum area.
When a device capable of driving a chain or the like is separately installed at an appropriate position and the chain is driven, each rotor blade rotates to generate lift by wind power. As a result, the aircraft floats when it reaches a lift higher than the aircraft load, stops in the air when the aircraft load and lift balance, and descends and landings almost vertically based on the principle that the aircraft descends when the aircraft load exceeds the lift. I found that I could provide a possible aircraft.

発明の効果The invention's effect

本体構造が大変単純で、躯体制作費も大幅に削減可能で、且つ小馬力の動力で飛行することができ、離着陸に大きな場所を必要とすることもないので、近距離用及び自家用航空機として利用できる。  The body structure is very simple, the cost of building the body can be greatly reduced, it can fly with small horsepower, and it does not require a large place for takeoff and landing, so it can be used as a short-distance and private aircraft it can.

広大な滑走路を伴う飛行場を必要とせず、ジェットの様な騒音が無く、ヘリコプターの様な複雑な機構が無く、庭先から離陸しても砂塵を巻き上げないので、平面交通の為事故が多発している自動車に代わって、次世代自家用機として最適である。
本機はヘリコプターの様に地面（水面）に風圧を吹き掛けないし、飛行艇の様に離着陸に水面を滑走する必要がない。よって、駆動装置、下方の回転翼等は機体内にあり、機体下部（後退翼軌道外側）全体をボートの様に防水水密にする事により、空中飛行は勿論、滑走路不要の為に自宅庭先、水草の繁った湖、雪上斜面、砂漠等あらゆる場所から垂直離着陸が自由自在に行う事が出来る、三位一体型の新規航空機である。
水密にする事により、その下にタンクを設置し、山林消火農薬散布等に利用でき、垂直離着陸のメリットで風波の荒天でも飛行艇より迅速に対応出来る。
連結機は大量に貨物が輸送できるので、工場から他の工場へ直接部品の搬送が短時間で出来る。他のメリットとして、連結機体間の固定翼は上昇、下降時に揚力を調整補助したり、前後の重量バランスをスライドさせて調整等を行うことが出来る。
旋回時の安定、又は左右バランスの為に左、右機体の回転翼の回転数を可変調整出来る。又、この連結機の場合、操縦室を独立別区画にする事が出来る。There is no need for an airfield with a vast runway, no noise like a jet, no complicated mechanism like a helicopter, and even when taking off from the garden, dust does not roll up. It is ideal as a next-generation private machine instead of a conventional car.
This aircraft does not blow wind pressure on the ground (water surface) like a helicopter, and does not need to glide on the water surface for take-off and landing like a flying boat. Therefore, the drive unit, lower rotor blades, etc. are inside the aircraft body. By making the entire lower part of the aircraft (outside of the retracted wing trajectory) waterproof and watertight like a boat, you can fly in the air and avoid the runway. This is a new trinity type aircraft that can freely take off and land from any place such as a lake with aquatic plants, snowy slopes, and deserts.
By making it watertight, a tank can be installed under it and used for spraying forest fire extinguishing pesticides, etc. It can respond more quickly than flying boats even in stormy wind waves due to the advantage of vertical takeoff and landing.
Since the coupling machine can transport a large amount of cargo, parts can be transported directly from one factory to another in a short time. As other merits, the fixed wings between the connecting machine bodies can be adjusted and assisted by adjusting the lift when moving up and down or by sliding the weight balance between the front and rear.
The rotational speed of the rotor blades of the left and right aircraft can be variably adjusted for stability during turning or left / right balance. In the case of this coupling machine, the cockpit can be divided into separate sections.

第１図
左右両側の軌道壁（濃色）内を右側前方に複数の回転翼を平行回転させて揚力を発生させる。単機の右上前から見た全体図Fig. 1 Lifting force is generated by rotating a plurality of rotor blades in parallel on the right front in the left and right track walls (dark color). Overall view seen from the top right of the single unit

第１図
単機の右上前から見た全体図
第２図
二台連結機から回転翼を省略して、左上後から見た全体図
第３図
翼断面の４図。主軸、副軸、中央軸等の色々な取付位置、方法を示す。
第４図
副軸の直線自在溝と曲線自在溝を示す。
第５図
主軸、副軸式の回転翼平面（Ｓ＝３／１０）、及び断面図見本です。
第６図
中央凹面回転翼の平面、正面、側断面図見本です。
第７図
上図は回転翼の方向転換を行わない場合の回転軌道図です。
（左前方、右後方）
下図は回転翼の下方後退時（左側）と上方前進に切り替わる時点（右側）で方向転換を行う場合の回転軌道図です。
第８図
スイング用副軸軌道図。
第９図
前進通過時の上下に分かれた主軸、副軸分離軌道図。
第１０図
上図は回転翼の前進下降時の第２副軌道図です。前進下降用副軸軌道を前方に移し、揚力の方向が前方、前進に向く様にしたもの。
下図は二連結機間の中間固定翼を示す断面図。揚力補助、離着陸調整及び前後のバランス調整翼。
第１１図
「左」は回転翼約半分の平面図です。「中」は上仕切隔壁板で、「右」は下仕切隔壁板で、上下翼表面の空気速度を均一にしてバイパス部に開放する。
第１２図
単機の回転翼を左後方から見た姿図です。
第１３図
中央軌道式壁（図上それぞれの中央軌道式回転翼を連結してセットする）の後ろから見た図
第１４図
上図はバイパス部内の固定翼を除いた圧縮空気噴出口図です。
下図は固定翼の付いたバイパス部です。
第１５図
上図は圧縮空気噴出状態の圧縮空気噴出口図です（上部流入口筒の一部カット）。
下図は閉鎖し内部接触面が膨張した水密状態。
第１６図
単機の軌道壁を除いて出入口ドアをオープンし、ステップが手前に引き出された状態。又外側水密区画部と内側居住区画部を分離した図。（軌道壁、回転翼除く）
第１７図
単機の少人数用に内側居住区画部を縮小した図。（軌道壁、回転翼除く）
第１８図
右旋回時にサイド前翼と上方軌道壁下部の固定翼を対地平行に保った状態。（回転翼除く）FIG. 2 is a general view as seen from the front right top of FIG. 1. FIG. 2 is a general view of the cross section of the blade shown in FIG. Various mounting positions and methods such as the main shaft, sub shaft, and center shaft are shown.
Fig. 4 shows a straight groove and a curved groove on the countershaft.
Fig. 5 Main shaft, countershaft type rotor blade plane (S = 3/10), and cross section sample.
Fig. 6 is a sample of the plane, front and side cross-section of the central concave rotor.
The upper figure in Fig. 7 shows the rotation trajectory when the direction of the rotor blades is not changed.
(Left front, right rear)
The figure below shows the rotation trajectory when changing direction when the rotor blades are moving backward (left) and when moving forward (right).
FIG. 8 is a secondary axis trajectory for swing.
FIG. 9 is an orbit diagram of the main shaft and the sub shaft separated when moving forward.
The upper figure of Fig. 10 is the second sub-orbit diagram when the rotor blades are moving forward and lower. The forward and lower countershaft track is moved forward so that the direction of lift is directed forward and forward.
The lower figure is a cross-sectional view showing the intermediate fixed blade between the two coupling machines. Lift assistance, take-off and landing adjustment and front and rear balance adjustment wings.
Fig. 11 “Left” is a plan view of about half of the rotor blades. “Middle” is the upper partition wall plate, and “Right” is the lower partition wall plate, making the air velocity on the upper and lower blade surfaces uniform and opening to the bypass section.
Fig. 12 is a view of the rotating blade of a single machine as seen from the left rear.
Fig. 13 View from the back of the central track type wall (connecting and setting each central track type rotary blade on the figure) .
The figure below shows the bypass section with fixed wings.
The upper part of Fig. 15 is a compressed air outlet view of the compressed air ejection state (part of the upper inlet tube).
The figure below shows a watertight state with the internal contact surface expanded and closed.
Fig. 16 A state where the door is opened except for the track wall of the single machine, and the step is pulled forward. Moreover, the figure which isolate | separated the outer side watertight division part and the inner side residence division part. (Excluding track wall and rotor blade)
FIG. 17 is a diagram in which the inner living compartment is reduced for a small number of single machines. (Excluding track wall and rotor blade)
FIG. 18 shows a state in which the side front wing and the fixed wing below the upper track wall are kept parallel to the ground when turning right. (Excluding rotor blades)

符号の説明Explanation of symbols

１ 回転翼の主軸
１ａ 回転翼の副（末尾）軸
１ａ１ 副軸直線自在溝
１ａ２ 副軸曲線自在溝
１ｂ 回転翼の中間軸
２ 回転翼
２ａ 上方前進回転翼
２ｂ 下方後退回転翼
２ｃ 前方前進下降回転翼
２ｄ 進入角度の変化した回転翼
２ｅ 回転翼方向転換時
２ｆ 後方前進上昇回転翼
２ｇ 中央軌道式回転翼
３ 主軸用軌道
３ａ 副軸用軌道
３ａ１ スイング用副軸用軌道
３ａ２ 前進通過時の主軸、副軸分離軌道
３ｂ 前進用第２副軸軌道
４ 軌道壁
４ａ 上方前進軌道壁
４ｂ 下部後退軌道壁
４ｃ 中央軌道壁
５ 翼上下の仕切隔壁板
５ａ 上仕切隔壁板
５ｂ 下仕切隔壁板
５ｃ 上隔壁風圧制御板
５ｄ 下隔壁風圧制御板
６ 外側水密区画部
６ａ 前車輪格納庫
６ｂ 後車輪格納庫
６ｃ 山林消火農薬散布用タンク
７ 内側居住区画部
７ａ 大人数用居住区
７ｂ 少人数用居住区
８ 機体横の固定翼
８ａ 旋回時の横固定翼
９ 軌道壁上下の固定翼
９ａ 旋回時の壁下固定翼DESCRIPTION OF SYMBOLS 1 Rotating blade main shaft 1a Rotating blade auxiliary (tail) shaft 1a1 Rotating blade linear free groove 1a2 Rotating blade intermediate groove 2b Rotating blade intermediate shaft 2 Rotating blade 2a Upper forward rotating blade 2b Lower backward rotating blade 2c Forward forward descending rotation Blade 2d Rotor blade 2e with changed approach angle 2e When rotating blade direction change 2f Backward ascending rotor blade 2g Central track type rotor blade 3 Main shaft track 3a Sub shaft track 3a1 Swing sub shaft track 3a2 Main shaft during forward passage, Secondary shaft separation track 3b Advance second counter shaft track 4 Track wall 4a Upper travel track wall 4b Lower retraction track wall 4c Central track wall 5 Upper and lower partition partition plate 5a Upper partition partition plate 5b Lower partition partition plate 5c Upper partition wind pressure Control plate 5d Lower bulkhead wind pressure control plate 6 Outer watertight compartment 6a Front wheel hangar 6b Rear wheel hangar 6c Mountain forest fire extinguishing pesticide spray tank 7 Inner residential compartment 7a Large residential area 7b Small residential area 8 Wall under the fixed wing at a fixed wing 9a pivoting of the lateral fixed wing 9 orbital wall vertically at the body side of the fixed vanes 8a turning

Claims (8)

飛行物体の左右両側（又は中央）に多数の回転翼を収容する軌道を設け、回転翼両端の（又は中央）前部でチェーン等の駆動部に一定間隔で固定連結し、これを主軸として主軸用軌道内を回転させる。
飛行物体の全体を覆う形で回転翼面を平行回転させ、該回転翼の後部を支持するベアリング、タイヤ等の副軸又は中央軸等の通る軌道から構成される。
上部軌道壁を飛行本体と上下に分離する事により、軌道壁の後半の回転翼上昇部及び前半の下降部に於いても回転翼後部副軸等は前後翼同士を連結していないので、副軸軌道の任意な位置設定によって揚力発生が出来る装置及びチェーン等の駆動装置を有し、それを駆動できる装置を別途適当な位置に設置した垂直離着陸自在機。A trajectory that accommodates a large number of rotor blades is provided on both the left and right sides (or center) of the flying object, and is fixedly connected to a drive unit such as a chain at a fixed interval at the front (or center) ends of the rotor blades. Rotate in the trajectory.
The rotary blade surface is rotated in parallel so as to cover the entire flying object, and is composed of a bearing that supports the rear part of the rotary blade, a secondary shaft such as a tire, or a track passing through a central shaft or the like.
By separating the upper track wall from the top and bottom of the flight body, the rotor blade rear countershaft and the like are not connected to each other even in the rotor blade ascending part and the former part of the lower part of the orbital wall. A vertical take-off and landing aircraft that has a device capable of generating lift by setting an arbitrary position of the shaft track and a drive device such as a chain, and a device that can drive the device is separately installed at an appropriate position. 飛行本体下部を後退時に発生する圧縮された空気はバイパス部で開放し、翼の上下壁では仕切隔壁板を変化させて空気を分散させ、又は仕切隔壁板を均一板にして回転翼と接近させ、上下の面風速を均等にするバイパス装置。
上仕切隔壁板及び下仕切隔壁板から流れて来た圧縮空気はバイパス部の下方に噴出、又は後方に噴出させ、離陸を補助する。又は後部回転翼立ち上がり部に吹き出し、回転翼末尾（副軸側）の立ち上がりを補助する。
噴出口は外側からの水圧等が懸かる時は内部膨張して水密を保ち、バイパス部からの圧力で開放し、圧縮空気噴出する。噴出口の上部流入口はＷ・Ｌ（水面）より上にする。又、主に水上、雪上等での使用の場合は下方噴出口は閉鎖するか付けない。The compressed air generated when retreating the lower part of the flight body is released at the bypass, and the partition walls are changed on the upper and lower walls of the wings to disperse the air, or the partition walls are made uniform to approach the rotor blades. A bypass device that equalizes the upper and lower surface wind speeds.
The compressed air that has flowed from the upper partition wall plate and the lower partition wall plate is ejected below or below the bypass portion to assist takeoff. Or, it blows out to the rising part of the rear rotor blade, and assists the rising of the rear end (secondary shaft side) of the rotor blade.
When the water pressure or the like from the outside is applied, the jet port expands internally to keep water tight, opens with the pressure from the bypass part, and jets compressed air. The upper inlet of the jet outlet is above W · L (water surface). Also, when used mainly on water, on snow, etc., the lower jet outlet is closed or not attached. 前進の方法は前進用駆動源を併用する他に、尾翼調整により機体後部を持ち上げたら前進する事が出来るが、軌道壁の前半の下降部に於いて主軸、副軸軌道間に別の副軸用軌道を設け、それに切り替えて回転翼を前傾姿勢にする事により前方に揚力が発生し前進する事が出来る、前進用の第２副軌道装置。  In addition to using a forward drive source together with the forward drive method, you can move forward by lifting the rear part of the fuselage by adjusting the tail, but in the lower part of the first half of the track wall, there is a separate secondary shaft between the main and secondary shaft tracks. A second sub-orbit device for advancing that can move forward by generating a lifting force by providing an orbit and switching to a forward-tilt posture. 垂直翼は後半の左右回転翼上昇軌道壁の後方に添わせて取り付ける。
又、中央付近の上部軌道壁と外側水密区画部間、及び前半の下降部軌道壁の後方に取り付ける事が出来る方向制御垂直翼。Install the vertical wings along the rear of the left and right rotor blades.
A directional control vertical blade that can be attached between the upper track wall near the center and the outer watertight compartment, and behind the lower track wall in the first half. 回転翼の副軸又は中央軸等が揚力発生中の露出軌道壁を通過時にスイング用副軸軌道を通過させ、回転翼の後半部や末端を魚体の推進の様にくねらせ、波動運動を上下に起こす事により、前進を補助するスイング用副軌道。  When the secondary shaft or the central shaft of the rotor blade passes through the exposed orbit wall where lift is generated, the secondary shaft orbit for swinging is passed, and the latter half or the end of the rotor blade is twisted like a fish propulsion to move the wave motion up and down. A secondary orbit for swing that assists the forward movement by waking up. 副軸等を回転翼に固定せず前後、上下等に自在に動ける溝を作り、揚力発生角度の調整及び回転翼下方後退時の収納状態の調整を行う曲線（又直線）自在溝。  A curved (or straight) free groove that adjusts the lift generation angle and the retracted state when the rotor blade is retracted downward by creating a groove that can freely move back and forth, up and down, etc. without fixing the countershaft etc. to the rotor blade. 居住区（貨物室等）を本体（回転翼軌道壁等）と離し、吊り下げるか横又は下部等から弾性体等で支えて、旋回時遠心力制御、及び回転翼が方向転換する時の振動やスイング用副軸軌道通過時の振動を防止すると共に居住性、機内移動等を良好にする為の本体分離機構。  Separate the residential area (cargo compartment, etc.) from the main body (rotor blade track wall, etc.), suspend or support it with an elastic body from the side or bottom, etc., control centrifugal force during turning, and vibration when the rotating blade changes direction A body separation mechanism that prevents vibration when passing through the orbital axis of the swing and improves comfort and movement within the machine. ２機以上の機体を横に並べ、上方前進軌道壁間等に長い固定翼（単機時の構造補強と旋回時に水平保持の調整等を行う翼等）を延長し取付る、又機体下部同士も固定し複数機体を横に連結し、乗客数、貨物量に応じて増設可能な連結機体。  Arrange two or more aircrafts side by side, and extend and install long fixed wings (such as wings that reinforce the structure of a single aircraft and adjust the horizontal holding during turning) between the upper forward track walls. A connecting machine that can be fixed according to the number of passengers and cargo volume.

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