JP7104427B2 - Winged drone - Google Patents

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JP7104427B2
JP7104427B2 JP2020032472A JP2020032472A JP7104427B2 JP 7104427 B2 JP7104427 B2 JP 7104427B2 JP 2020032472 A JP2020032472 A JP 2020032472A JP 2020032472 A JP2020032472 A JP 2020032472A JP 7104427 B2 JP7104427 B2 JP 7104427B2
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義郎 中松
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義郎 中松
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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
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    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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本発明は垂直離着陸ができ且つ高速に水平飛行できる新型ドローン等航空機に関する。 The present invention relates to a new type of drone or other aircraft capable of vertical takeoff and landing and horizontal flight at high speed.

通常の飛行機は、飛行機が離陸できるような速度になるまで滑走路を滑走する。また、逆に着陸する場合にも、着陸してから停止するまでの間滑走するので滑走路が必要となる。一般の距離は１．５ｋｍから３ｋｍ程度のものが必要である。そこで、ＶＴＯＬ（垂直離着陸機）が必要となる。
この種の飛行機としては、ヘリコプタ，オスプレイ，ドローンなどが知られている。ヘリコプタは、図１に示す如く１個のプロペラをホバリング、上昇、下降、水平飛行のそれぞれに対して用いるものである。図１において、１は機体、３はテイルロータ、３２はプロペラ回転用モータである。 A normal plane runs on the runway until it is fast enough to take off. Also, when landing on the contrary, a runway is required because it slides from landing to stopping. The general distance needs to be about 1.5 km to 3 km. Therefore, VTOL (vertical takeoff and landing aircraft) is required.
Helicopters, Ospreys, drones, etc. are known as this type of airplane. As shown in FIG. 1, the helicopter uses one propeller for hovering, ascending, descending, and level flight. In FIG. 1, 1 is an airframe, 3 is a tail rotor, and 32 is a propeller rotation motor.

ヘリコプタは水平速度が遅いので、水平速度が速いオスプレイ（図２）が開発された。オスプレイは、１９５３年本発明者が発明したものであり、これをベルエアクラフト社のＣＥＯロウレンス・ベル氏に教授し、ベルエアクラフト社が近年になりようやく実用化したものである。
主翼の両端にティルト制御が可能なプロペラを持ち、このプロペラのティルト角を制御することで、ホバリング機能や、水平飛行が可能となっている。上昇と直進動作を行うために、プロペラのティルト角を０度から９０度まで変化させる。しかしロータを水平、垂直にする変換時に多くの事故が発生する。
図２において、１は機体、３４はオスプレイ上昇・下降・前進用プロペラ、４は水平尾翼、５はオスプレイエンジン用回転軸、３３はオスプレイプロペラ用エンジンであるが近年ようやくポピュラーになった。
図３は公知のドローンであり、これも１９４０年に本発明者が発明したものであるが、近年ようやくポピュラーになった。図３において、６はドローンプロペラ、７はドローン上昇・下降用モータ、８はドローンプロペラガイド、９は受信装置・カメラ等である。 Since the helicopter has a slow horizontal velocity, an Osprey with a high horizontal velocity (Fig. 2) was developed. The Osprey was invented by the present inventor in 1953, which was taught to CEO Lawrence Bell of Bell Aircraft, and was finally put into practical use by Bell Aircraft in recent years.
It has propellers that can control tilt at both ends of the main wing, and by controlling the tilt angle of this propeller, hovering function and level flight are possible. The tilt angle of the propeller is changed from 0 degrees to 90 degrees in order to perform ascending and straight movements. However, many accidents occur when converting the rotor to horizontal and vertical.
In FIG. 2, 1 is an airframe, 34 is an Osprey ascending / descending / advancing propeller, 4 is a horizontal stabilizer, 5 is a rotating shaft for an Osprey engine, and 33 is an engine for an Osprey propeller, but it has finally become popular in recent years.
FIG. 3 is a known drone, which was also invented by the present inventor in 1940, but has finally become popular in recent years. In FIG. 3, 6 is a drone propeller, 7 is a drone raising / lowering motor, 8 is a drone propeller guide, and 9 is a receiving device / camera and the like.

前述したように、滑走路が無い場所では飛行機は離着陸出来ない。通常の飛行機は垂直離着陸やホバリング機能は有していない欠点がある。このような問題を解決するために、垂直離着陸やホバリング機能を持つ飛行体が考えられた。ヘリコプタは、垂直離着陸とホバリング機能を有する飛行体であり、海難事故や山での遭難事故等で、人命救助に活躍しているが、しかし、水平飛行速度が遅く、また、航続距離も短く、積載荷物量も少ないので、ヘリコプタに代わる飛行体が求められている。
オスプレイ型の飛行機の場合、垂直離着陸時にプロペラの風が翼を叩き、空力的に非効率となっている。
また、図３の如きドローンが公知であるが、ドローンは水平飛行速度が遅く長距離飛べないし、横風でひっくり返ったり全天候型でないので、アマゾン等が計画しているが荷物配送や、急速輸送としては向いていない。 As mentioned above, airplanes cannot take off or land in places where there is no runway. Normal airplanes have the drawback of not having vertical takeoff and landing or hovering functions. In order to solve such a problem, an air vehicle having vertical takeoff and landing and hovering functions was considered. A helicopter is an aircraft that has vertical takeoff and landing and hovering functions, and is active in saving lives in marine accidents and mountain accidents, but its horizontal flight speed is slow and its cruising range is short. Since the load capacity is small, there is a need for an air vehicle to replace the helicopter.
In the case of Osprey-type airplanes, the wind of the propeller hits the wings during vertical takeoff and landing, making it aerodynamically inefficient.
In addition, although drones as shown in Fig. 3 are known, drones have slow horizontal flight speeds and cannot fly long distances, and they are not all-weather type or overturned by crosswinds. Not suitable for.

前記した課題を解決する本発明は、垂直上昇下降用前進用プロペラと水平飛行用安定翼を設けて構成する。これは垂直上昇下降が出来ないオートジャイロとも異なる手段である。 The present invention that solves the above-mentioned problems is configured by providing a propeller for advancing vertically ascending and descending and a stabilizing wing for horizontal flight. This is a different method from the autogyro, which cannot move up and down vertically.

本発明によれば、水平速度が速く、遠距離を小エネルギで積載量も多くなり、全天候型であり、安全で安定な垂直離着陸やホバリング機能を持ち離陸上昇時にプロペラ風が翼を打つ翼力ロスが無くティルトロータも不要で制御構造が簡単になり、また事故もなくなり、製造容易でローコストの、通販の商品輸送をエネルギ高効率で高速で遠距離に確実に配送できる垂直離着陸型高速長距離安全飛行機を提供することができ、産業上時間節約と主深効果を生み出す画期的発明である。 According to the present invention, the horizontal speed is high, the load capacity is large at a long distance with low energy, it is an all-weather type, it has a safe and stable vertical takeoff and landing and hovering function, and the propeller wind hits the wings when the takeoff rises. No loss, no tilt rotor, simple control structure, no accidents, easy to manufacture, low cost, vertical takeoff and landing type high speed long distance that can reliably deliver mail order goods with high energy efficiency, high speed and long distance It is an epoch-making invention that can provide a safe aircraft, saves industrial time and produces a main profound effect.

公知のヘリコプタの側面図Side view of a known helicopter 公知のティルトロータ型（オスプレイ）の側面図Side view of a known tilt rotor type (Osprey) 公知のドローンの平面図Top view of a known drone 本発明のドローンとしての実施例を示す平面図Top view showing an embodiment as a drone of the present invention 本発明の第２実施例無尾翼ドローンの平面図Top view of the second embodiment of the present invention, a tailless drone 本発明の第３実施例先尾翼型の平面図Plan view of the canard type according to the third embodiment of the present invention 本発明第４実施例串型機平面図Top view of the skewer type machine according to the fourth embodiment of the present invention 本発明第５実施例の平面図Top view of the fifth embodiment of the present invention 本発明第６実施例のソーラープレーンThe solar plane of the sixth embodiment of the present invention 本発明第７実施例7th Example of the present invention 本発明第８実施例（実機）側面図Side view of the eighth embodiment (actual machine) of the present invention 本発明の第９実施例双発型9th Example of the Present Invention Twin-engine type

本発明はこのような課題に鑑みてなされた新発明航空機であり、上昇下降用プロペラと前進用プロペラと回転または回転しない水平飛行用翼を設け垂直離着陸やホバリングできることは勿論のこと、水平飛行速度が速く、エネルギロスが少なく長距離を飛べて全天候型で悪天候でも安定な飛行を行うことができる新垂直離着陸型飛行機（新ＶＴＯＬ）を提供することを目的としている。
本発明は従来のドローンとも、ヘリコプタとも、オスプレイとも、オートジャイロとも異なる発想である事に注目すべきである。 The present invention is a newly-invented aircraft made in view of such a problem, and is capable of vertical takeoff and landing and hovering by providing an ascending / descending propeller, a forward propeller, and a horizontal flight wing that does not rotate or rotate, as well as a horizontal flight speed. The purpose is to provide a new vertical take-off and landing aircraft (new VTOL) that is fast, has little energy loss, can fly long distances, and can fly stably even in bad weather in all weather types.
It should be noted that the present invention is different from conventional drones, helicopters, Ospreys, and autogyros.

図４は本発明発明航空機第１実施例の平面図である。図において、１３は水平尾翼、１４は垂直尾翼、１０は前進用プロペラである。１２は水平飛行用主翼で上昇用プロペラガード８と主翼桁１５により支えられている。６は上昇・下降用ホバリング用プロペラである。
これら主翼１２と主翼桁１５は、プロペラガード８の左右に一対設けられている。
１４はプロペラガード８の後部に設けられた水平尾翼、１３はプロペラガード８に支えられた舵取り用垂直尾翼である。７はホバリング用プロペラ６を回転させるモータである。９は撮影用カメラと電子回路、電池等である。
本発明航空機は上昇プロペラを邪魔しないで、主翼１２、尾翼１３、前進プロペラ１０を設け、水平飛行速度を高速化できることと、プロペラガード８を利用し、前進プロペラ１０、回転モータ１１、主翼１２、尾翼１３、１４を構造的に支え共用する本発明第１実施例である。 FIG. 4 is a plan view of the first embodiment of the aircraft of the present invention. In the figure, 13 is a horizontal stabilizer, 14 is a vertical stabilizer, and 10 is a forward propeller. Reference numeral 12 denotes a main wing for horizontal flight, which is supported by a propeller guard 8 for ascending and a main wing girder 15. Reference numeral 6 denotes a hovering propeller for ascending / descending.
A pair of the main wing 12 and the main wing girder 15 are provided on the left and right sides of the propeller guard 8.
Reference numeral 14 denotes a horizontal stabilizer provided at the rear of the propeller guard 8, and reference numeral 13 denotes a vertical stabilizer for steering supported by the propeller guard 8. Reference numeral 7 denotes a motor for rotating the hovering propeller 6. Reference numeral 9 denotes a camera for photographing, an electronic circuit, a battery, and the like.
The aircraft of the present invention is provided with a main wing 12, a tail wing 13, and a forward propeller 10 without interfering with the ascending propeller, and can increase the horizontal flight speed. Using the propeller guard 8, the forward propeller 10, the rotary motor 11, the main wing 12, This is the first embodiment of the present invention in which the tail wings 13 and 14 are structurally supported and shared.

図５は本発明第２実施例で無尾翼ドローンの平面図である。翼桁１５、主翼２０、昇降舵１６、翼端垂直方向腕１７、後方にプッシュプロペラ１８、駆動モータ１９を設けた本発明第２実施例の平面図である。本発明の趣旨は、図４で説明した通りである。 FIG. 5 is a plan view of a tailless drone in the second embodiment of the present invention. FIG. 5 is a plan view of a second embodiment of the present invention in which a spar 15, a main wing 20, an elevator 16, a wing tip vertical arm 17, a push propeller 18 and a drive motor 19 are provided at the rear. The gist of the present invention is as described with reference to FIG.

図６は本発明先尾翼型実施例で、プロペラガード１３で支えられた先尾翼桁２２とプロペラガード８で支えられた先尾翼２１とプロペラ用モータ１１とプルプロペラ１０、プロペラカード８で支えられた主翼桁３５と主翼３１とプロペラガード８で支えられたプッシュ式プロペラ１８の駆動モータ１９、主翼翼端の垂直尾翼３０からなる。 FIG. 6 shows a canard type embodiment of the present invention, which is supported by a canard girder 22 supported by a propeller guard 13, a canard 21 supported by a propeller guard 8, a propeller motor 11, a pull propeller 10, and a propeller card 8. It is composed of a main wing girder 35, a main wing 31, a drive motor 19 of a push-type propeller 18 supported by a propeller guard 8, and a vertical tail wing 30 at the tip of the main wing.

図７は本発明第４の実施例でプロペラガード１３を設けないで、２つの主翼３６、３７をプロペラガードを兼用した発明で、前翼３６と後翼３７を同じ大きさの串型にした串型航空機である。即ち、両翼の間に上昇下降するプロペラ６とモータ７を設け、主翼３６、３７がプロペラ６の回転をガードする発明である。３８は翼外に設けた上昇下降プロペラモータ７の支持桁である。勿論、プロペラの数は増減しても本発明に含まれるものである。 FIG. 7 is an invention in which the propeller guard 13 is not provided in the fourth embodiment of the present invention, and the two main wings 36 and 37 are also used as the propeller guard. It is a skewered aircraft. That is, it is an invention in which a propeller 6 and a motor 7 that ascend and descend are provided between both wings, and the main wings 36 and 37 guard the rotation of the propeller 6. Reference numeral 38 denotes a support girder of the ascending / descending propeller motor 7 provided outside the wing. Of course, even if the number of propellers is increased or decreased, it is included in the present invention.

図８は本発明第５の実施例で、上下用プロペラ４つの回転軌跡３９を全部内接させ、プロペラガードを設けずに４枚の主翼２４と先尾翼２８と尾翼２９をプロペラガードに兼用させたものである。４０は４つのプロペラモータ７を結合する桁である。 FIG. 8 shows a fifth embodiment of the present invention, in which all four rotation loci 39 of the upper and lower propellers are inscribed, and the four main wings 24, the front tail wing 28, and the tail wing 29 are also used as the propeller guard without providing the propeller guard. It is a thing. Reference numeral 40 is a girder for connecting the four propeller motors 7.

図９は本発明の第６の実施例であって、４角型フレーム４１にプロペラモータ７、主翼４２を取り付けたもので、図８と同様であるが、主翼４枚をソーラーパネル４２にした実施例であり、太陽エネルギで永久に飛ぶ事もでき、地上にマイクロ波でエネルギを送れる。 FIG. 9 is a sixth embodiment of the present invention in which the propeller motor 7 and the main wing 42 are attached to the square frame 41, which is the same as in FIG. 8, but the four main wings are the solar panels 42. As an example, it can fly forever with solar energy and can send energy to the ground with microwaves.

図１０は本発明第７の実施例で、主翼４３、４４の外側に上下用プロペラ６とモータ７を設け、主翼構造をシンプル化した実施例である。
図４、図５、図６、図７、図８、図９、図１０に示すように構成された飛行機航空機の動作を説明すれば、以下の通りである。
この場合、先ず操縦者がリモコンでスイッチ１（図示せず）をオンにすると、無線によりドローンの上昇用モータ７、上昇用プロペラ６が回転を開始し、機体は所定の高度まで上昇する。次に、操縦者がリモコンスイッチ２（図示せず）をオンにすると、モータ１１、１９の回転力により前進用プロペラ７とプッシュプロペラ１８を回転させる。
機体は前進を開始し、浮力は図４の主翼１２と尾翼１３で、図５の２０、図６の２１と３１、図７の３６と３７、図８の２４、２８、図９の４２、図１０の４３、４４で分担しその間上昇用プロペラ６やモータ９は空転させる。そして、公知のドローンより高速で、目的地に到達するので物販や遠隔地の撮影に公知ドローンより優れている。
次に、着陸時の動作について説明する。着陸時には、操縦者が上下用プロペラ６全部の回転を上げ、前進用プロペラ１０の回転を停止する。この状態で上下用プロペラ６の回転を制御しながら着地する。
本発明によれば、着地時にプロペラのティルト角制御（図１の制御参照）やドローンの複数枚の水平プロペラの回転数の制御変更の回路や指令が不要となり、構造簡単となり、コストダウンと操作が簡単になり、着陸動作を安全確実に行うことができる。のみならず、水平用は固定翼を使用するので、高速飛行ができる。また翼をプロペラガードで兼用出来るので、構造簡単で軽量化出来る。 FIG. 10 is a seventh embodiment of the present invention, in which a vertical propeller 6 and a motor 7 are provided on the outside of the main wings 43 and 44 to simplify the main wing structure.
An airplane and an aircraft configured as shown in FIGS. 4, 5, 6, 7, 8, 8, 9, and 10 will be described as follows.
In this case, when the operator first turns on the switch 1 (not shown) with the remote controller, the drone's ascending motor 7 and the ascending propeller 6 start rotating wirelessly, and the aircraft ascends to a predetermined altitude. Next, when the operator turns on the remote control switch 2 (not shown), the forward propeller 7 and the push propeller 18 are rotated by the rotational force of the motors 11 and 19.
The airframe started to move forward, and the buoyancy was the main wing 12 and tail wing 13 in FIG. 5, 20 in FIG. 5, 21 and 31 in FIG. 6, 36 and 37 in FIG. 7, 24 and 28 in FIG. 8, 42 in FIG. 43 and 44 in FIG. 10 are shared, and the ascending propeller 6 and the motor 9 are idled during that time. And since it reaches the destination at a higher speed than the known drone, it is superior to the known drone for selling goods and shooting at remote locations.
Next, the operation at the time of landing will be described. At the time of landing, the operator increases the rotation of all the vertical propellers 6 and stops the rotation of the forward propeller 10. In this state, landing is performed while controlling the rotation of the vertical propeller 6.
According to the present invention, it is not necessary to control the tilt angle of the propeller (see the control in FIG. 1) or to change the control change of the rotation speed of a plurality of horizontal propellers of the drone at the time of landing, the structure is simplified, the structure is simplified, and the operation is reduced. Is easy, and the landing operation can be performed safely and reliably. Not only that, fixed wings are used for horizontal flight, so high-speed flight is possible. In addition, since the wings can also be used as a propeller guard, the structure is simple and the weight can be reduced.

図１２は双発の本願発明の実施例第９の平面図である。水平飛行は２発のプロペラ１０を具備しており、高速走行が可能であり且つ長距離移動することができる。垂直上昇下降用には４個のプロペラ６が設けられている。２１はエンジン１１間に設けられた桁、５３はエンジン１１と機構部５４間を接続する桁、５５は機構部５４間を接続する桁である。この発明も図１２に示すように、大勢の人を乗せる航空機として用いることができる FIG. 12 is a plan view of a ninth embodiment of the present invention of twin engines. The horizontal flight is equipped with two propellers 10, which enable high-speed travel and long-distance travel. Four propellers 6 are provided for vertical ascent and descent. 21 is a girder provided between the engines 11, 53 is a girder connecting the engine 11 and the mechanical portion 54, and 55 is a girder connecting the mechanical portions 54. As shown in FIG. 12, the present invention can also be used as an aircraft carrying a large number of people.

以上はドローンであるが、図１１は本発明実施例の第８で人が乗る実機でその側面図を示し、前進エンジン４６、同プロペラ４７、重心位置の胴体１に上昇下降兼用エンジン２５とロータ４８を設ける。垂直尾翼の５１、水平尾翼５０、操縦席２６である。前進用プロペラ４７とエンジン４６の代わりに後部にジェットエンジン又はロケットエンジン２７を設けた場合も本発明に含まれる。また、上昇下降用ロータ４８とそのエンジン３２を翼端８に設けた場合も勿論本発明に含まれる。念のために、オートジャイロというものがあるが、これは上昇下降エンジンが無く、本発明とは全く別物である。 The above is a drone, but FIG. 11 shows a side view of an actual machine on which a person rides in the eighth embodiment of the present invention. 48 is provided. There are 51 vertical stabilizers, 50 horizontal stabilizers, and 26 cockpits. The present invention also includes a case where a jet engine or a rocket engine 27 is provided at the rear instead of the forward propeller 47 and the engine 46. Further, of course, the case where the ascending / descending rotor 48 and its engine 32 are provided at the wing tip 8 is also included in the present invention. Just in case, there is an autogyro, but this is completely different from the present invention because it does not have an ascending / descending engine.

第９実施例までは翼を固定し、且つ前進用プロペラを別個に設けたものである。
第９実施例迄は上昇下降用のプロペラの後流が乱れないようにプロペラ後流部分に翼を配置していない。そして翼を固定している。また、前進用プロペラと上昇下降用プロペラと別に設けている。
また、第１実施例（図４）、第２実施例（図５）および、第３実施例（図６）は、水平飛行用固定翼が、４個以上の上昇前進兼用プロペラ用の複数のプロペラガードと結合しているドローンである。
さらに、第４実施例（図７）、第５実施例（図８）、第７実施例（図１０）、第９実施例（図１２）は、翼桁及び／または胴体を利用して、上昇下降用および前進用プロペラを搭載する翼を持ったドローンである。
Up to the ninth embodiment, the wings are fixed and the propeller for advancing is separately provided.
Until the ninth embodiment, the wings are not arranged in the wake portion of the propeller so that the wake of the propeller for ascending and descending is not disturbed. And the wings are fixed. In addition, a forward propeller and an ascending / descending propeller are provided separately.
Further, in the first embodiment (FIG. 4), the second embodiment (FIG. 5), and the third embodiment (FIG. 6), there are a plurality of fixed wings for horizontal flight for ascending / advancing propellers of four or more. It is a drone that is combined with a propeller guard.
Further, the fourth embodiment (FIG. 7), the fifth embodiment (FIG. 8), the seventh embodiment (FIG. 10), and the ninth embodiment (FIG. 12) utilize the spar and / or the fuselage. A winged drone equipped with ascending / descending and forward propellers.

本発明はドローンのみならず実機でも適用される。又、その場合、プロペラはエンジンで回転させる。又、プロペラでなく、ジェットエンジンやロケットを使用した場合でも本発明に含まれる。 The present invention applies not only to drones but also to actual machines. Also, in that case, the propeller is rotated by the engine. Further, even when a jet engine or a rocket is used instead of a propeller, it is included in the present invention.

本発明は、公知のドローンや公知のオスプレイ等ティルトロータ方式やヘリコプタ等、他の垂直離着陸機に比べ安全かつ水平速度が速い新型飛行機であり、現在のドローンでは通販等の長距離物品輸送やロジスティクスには速度が遅く長距離飛べず、エネルギを多く消費するので高速輸送に適さないが、本発明をドローンに適用した場合、物品を高速に輸送でき、長距離撮影が可能となり、また、本発明を人を載せる機体に適用した場合は、遠くの場所で急速な山岳救助、海難救助等に活躍するので、産業上大きな利用可能性がある。
また本発明の飛行機はヘリコプタに比較してピッチコントロール不要なので舵を簡単ローコストである上、水平速度が速く航続距離も長くまたオスプレイのティルトによる事故も皆無となるので安全であり、使用範囲が拡がる。また、その機体の大きさを大きくすれば、大勢の人を乗せることができ、また飛行場のない島にも就航することができ、島民の交通の不便さを補うことができ、防衛上、産業上の利用可能性が極めて大きい。
また本発明を成層圏付近に飛ばし、翼で受けた太陽エネルギをマイクロ波にして地上に送り、地上で電気エネルギとして使用すれば、無資源の我が国に貴重なエネルギを供給でき、また偵察衛星の代わりになる。防衛上、産業上の利用可能性が極めて大きい。 The present invention is a new type of airplane that is safer and has a faster horizontal speed than other vertical takeoff and landing aircraft, such as a known drone, a known tilt rotor system such as an Osprey, and a helicopter. It is not suitable for high-speed transportation because it is slow and cannot fly long distances and consumes a lot of energy. However, when the present invention is applied to a drone, goods can be transported at high speed, long-distance photography becomes possible, and the present invention also When applied to an aircraft carrying people, it can be used for rapid mountain rescue, marine rescue, etc. in distant places, so it has great industrial potential.
In addition, the airplane of the present invention does not require pitch control compared to the helicopter, so the rudder is easy and low cost, the horizontal speed is fast, the cruising range is long, and there is no accident due to the tilt of the Osprey, so it is safe and the range of use is expanded. .. In addition, if the size of the aircraft is increased, a large number of people can be carried, and it is possible to enter service on islands without airfields, which can compensate for the inconvenience of transportation for the islanders. The above availability is extremely high.
In addition, if the present invention is flown near the stratosphere, the solar energy received by the wings is converted into microwaves and sent to the ground, and used as electrical energy on the ground, valuable energy can be supplied to Japan, which has no resources, and can be used instead of reconnaissance satellites. become. Extremely defensive and industrial applicability.

１ 機体
２ メインロータ
３ テイルロータ
４ 水平尾翼
５ オスプレイエンジン用回転軸
６ ドローンプロペラ
６’ 同上（後部）
７ ドローン上昇下降モータ
７’ 同上（後部）
８ ドローンプロペラガード
９ 受信装置、カメラ等
１０ 前進用プロペラ
１１ 前進用プロペラモータ
１２ 主翼
１３ 水平尾翼
１４ 垂直尾翼
１５ 主翼桁
１６ 昇降用舵
１７ 翼端垂直昇降舵
１８ プッシュプロペラ
１９ プッシュプロペラ駆動モータ
２０ 無尾翼主翼
２１ 先尾翼
２２ 先尾翼桁
２３ 先尾翼型主翼
２４ プロペラガード兼用主翼
２５ 上昇下降プロペラ用エンジン
２６ 操縦室
２７ ジェット又はロケットエンジン
２８ プロペラ６ガード兼用先尾翼
２９ プロペラ６ガード兼用尾翼
３０ 翼端垂直尾翼
３１ 先尾型主翼
３２ プロペラ回転用モータ
３３ オスプレイプロペラ用エンジン
３４ オスプレイ上昇・下降・前進用プロペラ
３５ 先尾翼型の主翼桁
３６ プロペラ６ガード兼用串型主翼前翼
３７ プロペラ６ガード兼用串型主翼後翼
３８ 串型機に設けられた上下用プロペラモータ支持桁
３９ 上下用プロペラ回転軌跡
４０ ４つの上下用プロペラモータ７を結合する桁
４１ ４角型の桁で４つのプロペラモータ７を結合
４２ ソーラーパネル
４３ 串型主翼（翼端プロペラ付）前翼
４４ 串型主翼（翼端プロペラ付）後翼
４５ 胴体桁
４６ 実機前進プロペラエンジン
４７ 実機前進プロペラ
４８ 実機上昇下降専用ロータ
４９ 実機水平飛行専用主翼
５０ 実機水平飛行専用水平尾翼
５１ 実機水平飛行専用垂直尾翼
５２ 実機上昇下降専用ロータ用エンジン

1 Aircraft 2 Main rotor 3 Tail rotor 4 Horizontal stabilizer 5 Rotating shaft for Osprey engine 6 Drone propeller 6'Same as above (rear)
7 Drone ascending / descending motor 7'Same as above (rear)
8 Drone propeller guard 9 Receiver, camera, etc. 10 Forward propeller 11 Forward propeller motor 12 Main wing 13 Horizontal tail wing 14 Vertical tail wing 15 Main wing girder 16 Lifting steering wheel 17 Wing tip vertical lifting steering wheel 18 Push propeller 19 Push propeller drive motor 20 None Tail main wing 21 Tail wing 22 Tail wing girder 23 Tail wing type main wing 24 Propeller guard combined main wing 25 Ascending / descending propeller engine 26 Control room 27 Jet or rocket engine 28 Propeller 6 guard combined Tail wing 29 Propeller 6 guard combined tail wing 30 Wing tip vertical Tail wing 31 Tail type main wing 32 Propeller rotation motor 33 Osprey propeller engine 34 Osprey ascending / descending / advancing propeller 35 Tail wing type main wing girder 36 Propeller 6 guard combined skewer type main wing Front wing 37 Propeller 6 guard combined skewer type main wing Rear wing 38 Vertical propeller motor support girder provided on skewer machine 39 Vertical propeller rotation locus 40 Girder for connecting four vertical propeller motors 7 Combine four propeller motors 7 with a square girder 42 Solar Panel 43 Skew-shaped main wing (with wing tip propeller) Front wing 44 Skew-shaped main wing (with wing tip propeller) Rear wing 45 Body girder 46 Actual forward propeller engine 47 Actual forward propeller 48 Actual ascending / descending rotor 49 Actual horizontal flight main wing 50 Horizontal tail wing dedicated to actual horizontal flight 51 Vertical tail wing dedicated to actual horizontal flight 52 Engine for rotor dedicated to ascending and descending actual aircraft

Claims (5)

複数のプロペラガードを結合して一体とし、前記一体としたプロペラガードの接合部の谷間に翼桁を設けた事を特徴とする飛行体。 An air vehicle characterized in that a plurality of propeller guards are combined and integrated, and a spar is provided in the valley of the joint portion of the integrated propeller guards. 請求項１に於いて、プロペラガードに前進用モータ・プロペラを直接設けた事を特徴とする飛行体。 The flying object according to claim 1, wherein a forward motor / propeller is directly provided on the propeller guard. 請求項１に於いて、複数のプロペラガードを結合し一体とし、前記一体としたプロペラガードの前後に前進用と推進用モータ・プロペラを設け、かつ前記一体としたプロペラガードの左右に斜め後方に向けた翼桁及び翼を設けた事を特徴とする飛行体。 In claim 1, a plurality of propeller guards are combined and integrated, and forward and propulsion motor propellers are provided in front of and behind the integrated propeller guard, and diagonally rearward to the left and right of the integrated propeller guard. An air vehicle characterized by having a facing spar and wings. 請求項１に於いて、複数のプロペラガードを結合し一体とし、前記一体としたプロペラガードの左右に翼桁及び翼を設け、前方のプロペラガードに翼桁と翼を設け、かつ前記翼桁に前進用モータ・プロペラを設け、後方のプロペラガードに推進用モータ・プロペラを設けた事を特徴とする飛行体。
In claim 1, a plurality of propeller guards are combined and integrated, wing girders and wings are provided on the left and right sides of the integrated propeller guard, wing girders and wings are provided on the front propeller guard, and the wing girders are provided. An air vehicle characterized by having a forward motor / propeller and a propulsion motor / propeller on the rear propeller guard.
 請求項１に於て、翼面をソーラー電池とした事を特徴とする飛行体。
The flying object according to claim 1 , wherein the wing surface is a solar battery.
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