WO2000005131A1 - Vtol aircraft - Google Patents

Vtol aircraft Download PDF

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Publication number
WO2000005131A1
WO2000005131A1 PCT/JP1998/005666 JP9805666W WO0005131A1 WO 2000005131 A1 WO2000005131 A1 WO 2000005131A1 JP 9805666 W JP9805666 W JP 9805666W WO 0005131 A1 WO0005131 A1 WO 0005131A1
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Prior art keywords
aircraft
main wing
propeller
lift
wake
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PCT/JP1998/005666
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French (fr)
Japanese (ja)
Inventor
Takeshi Nishimoto
Eishi Nishimoto
Original Assignee
Takeshi Nishimoto
Eishi Nishimoto
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Priority claimed from JP24100198A external-priority patent/JP2002240797A/en
Application filed by Takeshi Nishimoto, Eishi Nishimoto filed Critical Takeshi Nishimoto
Publication of WO2000005131A1 publication Critical patent/WO2000005131A1/en

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B64C29/0025—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being fixed relative to the fuselage

Definitions

  • VTO L-type aircraft This invention relates to a VTOLI vertical take-off and landing aircraft with less power than a small airframe] Convenient, low body cost and low fuel consumption, stable and stable maneuverability Not only can be carried by door-to-door and used for practical equipment, but also used for solving social problems such as natural disasters, enhancing daily life, and leisure activities.
  • the VTO L can be cruised with about half the power of a helicopter.
  • the cruise can fly with the wings and thrust, and can cruise with the power of 14 times the weight of the aircraft, like an airplane. To do. From these, the aircraft cost will be less than 1Z2 for a helicopter, and to 1Z20 in the future The fuel consumption will be less than 1/4. This can be done by using two propellers (or propulsion) before and after the launch, using a catamaran and flaps.
  • a first object of the present invention is to make it possible to perform VTOL with power less than the weight of the aircraft and to reduce the cost of the aircraft and fuel consumption.
  • the second purpose is to make the flight stable, safe and easy to operate.
  • FIG. 1 is a three-dimensional view of an aircraft capable of performing VTOL.
  • FIG. 2 is a front view of an example of an experiment in which VTOL was performed with a power of 0.66 m of the aircraft.
  • FIG. 4 is a plan view and a side view of a trunk experiment example.
  • Fig. 5 is a front view of the single-seat demonstration machine
  • Fig. 6 is a plan view
  • Fig. 7 is a side view.
  • Fig. 8 is a front view of a lightweight aircraft
  • Fig. 9 is a plan view
  • Fig. 10 is a side view.
  • the sum of the thrust of the front and rear propellers is 0.66 of the aircraft weight.
  • Fig. 5 is a front view of a VT 0 L-type aircraft in which a person rides and steers with two propellers
  • Fig. 6 is a plan view
  • Fig. 7 is a trailing view
  • the specifications are shown in Table 1-2. .
  • a verification experiment of K2 0.66 is performed with T a 120 kg and Tb 50 kg. After this is done, we will experiment to make K smaller. Later, the thrust of the propeller was set to Tb -70 kg because when taking off, climbing, cruising, and landing, the aircraft was floating, the aircraft speed was reduced, the aircraft stopped at 0 Zs and was suspended in the air (hovering Landing safely.
  • Fig. 8 is a front view of a VT • L-type aircraft with a pneumatic propeller for stability and safety.
  • Fig. 9 is a plan view
  • Fig. 10 is a plan view
  • Fig. 1 is a three-dimensional view, using propellers (propellers) 1 and 2 before and after the main propeller 3. Rotate from the rear propeller 2 to raise the rear part of the aircraft and pull the aircraft backward. From that time, you can turn to V BOL 1 to get V TOL.
  • the upward force of the thrust of the two propellers 2 and the wind (the wake) of the front propeller 1 flow to the wing 3 to generate lift.
  • the wind (wake) of the propeller 2 prevents the turbulence at the trailing edge of the main body and separation, and the laminar flow improves the efficiency of lift.
  • the position of the center of gravity of the aircraft is preferably about 64% from the leading edge of the wing.
  • Figures 2, 3 and 4 show that in the experimental example, the upward force (lift + pressure) due to the wind (wake) at VTOL is 2.3 times higher than the upward force of the thrust of both propellers. V ⁇ 0 L was achieved at 66% of the aircraft weight.
  • an aircraft capable of V ⁇ 0 L with a power less than the weight of the fuselage is not only useful for industrial activities such as movement, logistics activities, rescue of life, fire fighting activities, In the event of a social problem such as the Great Hanshin Earthquake or a wildfire in Indonesia, it can be easily solved by using 10,000 aircraft. Helicopter Heichibu Yuichi is VTOL-friendly, but it always requires 1.2 times the power of the ⁇ weight, and one 5-seater aircraft costs 120 million yen and is expensive and easy to use.
  • this aircraft can use two of the propeller thrust and the wind (wake) power to produce V ⁇ 0 with about half the power of Ricoh in the evening, and cruises with thrust and wings like an airplane. It can fly at 1 ⁇ 4 of the aircraft weight.
  • VTOL can be made with about half the power of Helicopter in the evening, cruising can be less than 1/4 of the power, parts can be standard products instead of special products like helicopters, people can ride in the wing and the fuselage No need, power for ministry is less than half, engine is small, weight is about 2 23, light loading capacity is good, mass production is possible, and aircraft ⁇ is about 1 ⁇ 2 to 120 It will be cheaper.
  • Helicopter now costs 100 million'20 million yen for a helicopter It was about 200,000 yen, about 200,000 yen, and many people could use it as easily as a car, and millions to tens of millions of vehicles were used in each country. More than 10,000 aircraft can cooperate and solve social issues such as Indonesian forest fires immediately.

Abstract

A VTOL aircraft comprising propellers (1, 2) located at the front and rear of a main wing (3), the front propeller (1) being provided so that it pulls an airframe forward and a back wash by the propeller (1) provides a lift to the main wing (3), and the rear propeller (2) being provided so that the back wash by the rear propeller is directed toward the trailing edge of the main wing (3) in order to raise the airframe, and prevent a lift efficiency from being lowered due to separation of the back wash by the front propeller (1) from the upper surface of the main wing (3) ranging from near the center to the trailing edge so as to provide a big lift.

Description

明 細 書  Specification
VTO L型の航空機 技術分野 この発明は、 機体宽量以下の動力で V T O L I vertical take-off and landing aircraft垂直離着陸機] 出来便利で機体費も燃費も安く、 安定安 全で操縦もしゃすく人や物を Door To Doorで運び実用機に利用するのみ ならず、 地霹ゃ天災等の社会問題の解決や日常生活の充実、 レジャー坷 に利用出来ます。 Technical field of VTO L-type aircraft This invention relates to a VTOLI vertical take-off and landing aircraft with less power than a small airframe] Convenient, low body cost and low fuel consumption, stable and stable maneuverability Not only can be carried by door-to-door and used for practical equipment, but also used for solving social problems such as natural disasters, enhancing daily life, and leisure activities.
背景技術 現在、 ヘリコブ夕一は、 機体重量の 1. 2倍の動力がなければ、 VT OLも飛行も出来ない。 これで大きなエンジンや多くの燃料が必要で機体重量が重たく、 機 費が髙く使用燃料も多く使う必要があり、 5人乗りが 1機 1億 2千万円 もし、 1時間当たりの燃料費が 5万円もします。 これでは、 一般の人々はなかなか簡単に利用出来ない。 この発明は、 ブロペラが動力で回転されると空気に作用して、 風 （後 流） を作りその反作用で推力を得ます。 ヘリコプターは、 動力の内推力のみを利用して VTO Lや巡航してお りますが、 この VTO L型の航空機は VTO L時、 推力と風 （後流） の 2つの力を利用するので、 ヘリコプターの半分程の動力で VTO L出来 巡航は主翼と推力で飛び飛行機のように機 ίΦ重量の 1 4の動力で巡航 出来る。 します。 これらから機体費は、 ヘリコプターの 1 Z2以下、 将来は 1Z20に 燃費は 1/4以下になります。 これは、 主興の前後に 2つのブロペラ （又は推進力） を使い、 双胴と フラップを使うことで出来ます。 発明の開示 本発明の第一の目的は、 機体重量以下の動力で V TO L出来便利で機 体費も燃費も安く出来るようにするこ ある。 第二の目的は、 飛行時安定安全で簡単に操縦出来るようにすることで ある。 第三の目的は、 霡災ゃ山火事等の社会問題を解決し、 日常生活を充実 させ、 空のレジャーを楽しむことである。 図面の簡単な説明 第 1図は、 VTOL出来る航空機の立体図 第 2図は、 機体童量の 0. 66^きの動力で VTOL出来た実験例の正 面図であり、 第 3図や第 4図は胴実験例の平面図と側面図である。 BACKGROUND ART At present, Yuichi Helicopter cannot fly or fly VTOL unless it has 1.2 times the power of the body weight. This requires a large engine, a lot of fuel, a heavy aircraft weight, a high cost and a lot of fuel to be used, and a 5-seater car costs 120 million yen if the fuel cost per hour Costs 50,000 yen. This makes it difficult for the general public to use it easily. In this invention, when the propeller is rotated by power, it acts on the air to create wind (wake) and obtain thrust by the reaction. Helicopters use VTO L and cruise only by using the internal thrust of the power. This VTO L-type aircraft uses two forces, thrust and wind (wake), at VTO L. The VTO L can be cruised with about half the power of a helicopter. The cruise can fly with the wings and thrust, and can cruise with the power of 14 times the weight of the aircraft, like an airplane. To do. From these, the aircraft cost will be less than 1Z2 for a helicopter, and to 1Z20 in the future The fuel consumption will be less than 1/4. This can be done by using two propellers (or propulsion) before and after the launch, using a catamaran and flaps. DISCLOSURE OF THE INVENTION A first object of the present invention is to make it possible to perform VTOL with power less than the weight of the aircraft and to reduce the cost of the aircraft and fuel consumption. The second purpose is to make the flight stable, safe and easy to operate. The third purpose is to solve social problems such as disasters and wildfires, enhance daily life, and enjoy leisure in the sky. BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a three-dimensional view of an aircraft capable of performing VTOL. FIG. 2 is a front view of an example of an experiment in which VTOL was performed with a power of 0.66 m of the aircraft. FIG. 4 is a plan view and a side view of a trunk experiment example.
弟 5図は、 1人乗り実証試験機の正面図で第 6図は平面図で第 7図は 側面図である。 Fig. 5 is a front view of the single-seat demonstration machine, Fig. 6 is a plan view, and Fig. 7 is a side view.
第 8図は趦軽量飛行機の正面図で第 9図は平面図第 1 0図は側面図であ る。 夫' ' Γノリ1ノ W Δ izy、 i-ia lijs ίΐΐ) '図の仕様は、 表一 1の通りです。 Fig. 8 is a front view of a lightweight aircraft, Fig. 9 is a plan view, and Fig. 10 is a side view. Husband '' Γ ノ リ1ノ W Δ izy 、 i-ia lijs ίΐΐ) 'The specifications of the diagram are as shown in Table 11-1.
Figure imgf000005_0001
Figure imgf000005_0001
機体重量以下の動力で V TO Lするには、 前後のプロペラを 60回 巻いて地上に置き、 後のプロペラから回転させて、 機体後部が上がり 機体を後に引いた時に前のブロペラを回 $云さすと、 機体は滑走せずに 離陸します。  To perform V TOL with power less than the weight of the fuselage, wind the front and rear propellers 60 times, place them on the ground, rotate them from the rear propellers, rotate the rear part of the fuselage and rotate the front propeller when the aircraft is pulled backward. The aircraft will take off without gliding.
その時の機体重量と前後のプロペラの推力の和との比 （K) を求め ると、  When the ratio (K) between the weight of the aircraft at that time and the sum of the thrusts of the front and rear propellers is obtained,
K= (前後のプロペラの推力の和） /機体重量  K = (sum of thrust of front and rear propellers) / body weight
二 （57. 2 25 ) / \ 23. 5二 0. 66  Two (57.225) / \ 23.5 two 0.66
前後のプロペラの推力の和が、 機体重量の 0. 66です。 The sum of the thrust of the front and rear propellers is 0.66 of the aircraft weight.
なお、 この時、 機体は双胴とフラップ （主翼の下面より 60度） を セッ 卜し、 後のプロペラの回転軸角度は、 機体中心角 U 5度） と約 80度の時でした。 第 5図は 2つのプロペラを使い人が乗つて操縦して飛ぶ V T 0 L型の 航空機の正面図、 第 6図は平面図、 第 7図は惻面図で、 仕様は表一 2 に示す。 At this time, the fuselage was set with the twin fuselage and flaps (60 degrees from the lower surface of the main wing), and the rotation axis angle of the propeller later was about 80 degrees with the fuselage central angle U 5 degrees. Fig. 5 is a front view of a VT 0 L-type aircraft in which a person rides and steers with two propellers, Fig. 6 is a plan view, Fig. 7 is a trailing view, and the specifications are shown in Table 1-2. .
表一 2 1人乘りで操縦する V T 0 L型の航空機  Table 1 2 V T 0 L-type aircraft piloted by one person
Figure imgf000006_0001
実験機の実緝 Κ=0. 66以下でもで VTOL出来ることを確認す るが、 まず、 T a二 1 20 k g、 T b二 50 k g、 で K二 0. 66 の確認実験をする。 なお、 これが出来た後は、 さらに Kが小さくなる実験もする。 後のプロペラの推力を Tb -70 k gとしたのは、 離陸して上昇巡航 降下着陸する時に、 機体は浮いていて機体速度を減速して 0 Z sで 止まって空中に浮いている状態 （ホバリングの状態） にして. 安全に 着陸する。 第 8図は後のプロペラを安定安全の為に空気式にした V T◦ L型 の航空機の正面図、 第 9図は平面図， 第 1 0図は 面図で、 ί土様 は、 表一 3の通りです。
Figure imgf000006_0001
It is confirmed that VTOL can be achieved even if the actual machine of the experimental machine 以下 = 0.66 or less. First, a verification experiment of K2 0.66 is performed with T a 120 kg and Tb 50 kg. After this is done, we will experiment to make K smaller. Later, the thrust of the propeller was set to Tb -70 kg because when taking off, climbing, cruising, and landing, the aircraft was floating, the aircraft speed was reduced, the aircraft stopped at 0 Zs and was suspended in the air (hovering Landing safely. Fig. 8 is a front view of a VT • L-type aircraft with a pneumatic propeller for stability and safety. Fig. 9 is a plan view, Fig. 10 is a plan view, and Fig. 3
表一 3 1入乘りで後のブロペラが空気式の飛 ί亍機  Table 1 3 1 Riding propellers are pneumatic aircraft after entering
Figure imgf000007_0001
ここで、 V T O L時に主翼の上表面から空気を吸いそこに前のプロ ペラの風 （後流） を流すと主與が大きな揚力を得られ、 吸った空気で 機体の前後から吐出して重心の調節と後上向きに機 ί本をあげ、 後のブ 口ペラと同様の働きをし、 さらに一方のエンジンが止まった貯蔵して いた空気で安定安全に調整します。
Figure imgf000007_0001
Here, at VTOL, when air is sucked from the upper surface of the wing and the wind (wake) of the front propeller is flowed there, a large lift is obtained, and the sucked air discharges air from the front and rear of the aircraft and the center of gravity is discharged. Adjusting and lifting the machine upwards in the rear, the same function as the rear port propeller, and furthermore, one engine is stopped and stored air is adjusted stably and safely.
そして、 これを基準として幾何学的、 力学的、 運動学的相似性を応 用して、 2人乗りや 5人乗り、 1 0人乘りから 1 0 0入乗り等の V T O L出来る航空機が出来、 V T O L出来て便利で安く、 安定安全で簡 単に操縦出来ます。 発明を実施するための 良の形態 By applying geometric, mechanical, and kinematic similarities based on this, aircraft capable of VTOL such as two-seater, five-seater, ten-seater, and 100-seater rides are completed. VTOL is convenient, cheap, stable, safe and easy to operate. BEST MODE FOR CARRYING OUT THE INVENTION
本発明をより詳細に記述する為に添付図面に從ってこれを説明する。 第 1図は立体図で主與 3の前後にプロペラ （推進器） 1 、 2を使い. 後のプロペラ 2から回転して機体後部を上げ、 機 ί を後に引きます。 その時から、 前のブ口ベラ 1を回車云すると V T O L出来ます。  In order to describe the present invention in more detail, it will be described with reference to the accompanying drawings. Fig. 1 is a three-dimensional view, using propellers (propellers) 1 and 2 before and after the main propeller 3. Rotate from the rear propeller 2 to raise the rear part of the aircraft and pull the aircraft backward. From that time, you can turn to V BOL 1 to get V TOL.
それは、 両ブロペラし 2の推力の上向きの力と前のプロペラ 1の風 (後流） が主翼 3に流れ揚力を発生させます。  The upward force of the thrust of the two propellers 2 and the wind (the wake) of the front propeller 1 flow to the wing 3 to generate lift.
そして、 主與の後縁で乱れて剥離を起こすのを後のプロペラ 2の風 （ 後流） が防ぎ、 層流にして揚力の効率をよぐ'します。  Then, the wind (wake) of the propeller 2 prevents the turbulence at the trailing edge of the main body and separation, and the laminar flow improves the efficiency of lift.
また、 後のブロペラ 2で機体を後に引き、 それを前のプロペラ 1で前 進さすのにそれだれ大きな動力が必要なことは、 大きな風 (後流) を流 すことになり揚力がそれだけ大きくアップします。  Also, the fact that the propeller 1 pulls the fuselage backward and the propeller 1 moves forward requires more power, which means that a large wind (wake) will flow and the lift will increase accordingly. Up.
なお、 機体後部が上がることは、 V T O Lに加勢します。  Note that raising the rear of the aircraft will add to the VTOL.
—方、 主翼の下部に入ったプロペラ 1の風 （後流） は、 主翼 3と双胴 4、 フラップ 5、 地面に [用まれた所で、 フラップ 5と地面との間が小さ く、 ここから出ていく風 （後流） が なく、 主翼 3の下部に残り圧力が アップとなり、 機体を上にあげます。  —On the other hand, the wind (the wake) of the propeller 1 that entered the lower part of the main wing, the main wing 3 and the catamaran 4, the flap 5, and on the ground [where the flap 5 and the ground were small, There is no wind (wake) coming out of the wing, and the pressure remaining at the bottom of the wing 3 increases, raising the aircraft.
これを、 地面効果とも言います。  This is also called the ground effect.
これら推力の上向きの力と風 （後流） により新しく揚力と圧力の力が 加わり、 機体重量以下の動力で V T Oしが出来ます。  The upward force and wind (wake) of these thrusts add new lift and pressure forces, and VTO can be generated with power less than the weight of the aircraft.
この時、 機体の重心位置は主翼の前縁から 6 4 %程がよい。 第 2、 3、 4図は、 実験例で V T O L時の風 （後流） による上向き の力 （揚力 +圧力） の力が両プロペラの推力の上向きの力の 2 . 3 ίき で、 動力は機体重量の 6 6 %で V Τ 0 L出来ました。 産業上の利用可能性 At this time, the position of the center of gravity of the aircraft is preferably about 64% from the leading edge of the wing. Figures 2, 3 and 4 show that in the experimental example, the upward force (lift + pressure) due to the wind (wake) at VTOL is 2.3 times higher than the upward force of the thrust of both propellers. V Τ 0 L was achieved at 66% of the aircraft weight. Industrial applicability
以上のように、 本発明は機体重量以下の動力で V Τ 0 L出来る航空機 は、 ヘリコプターと同 こ J¾短時閒で移動や物流活動、 人命救助、 消火 活動の産業活動に役立つのみならず、 阪神大震災やインドネシアの山火 事等の社会問題が発生した時、 1万機も使え'ば、 簡単に解決出来ます。 それは、 ヘリコブ夕一は V T O L出来て ί更利ですが、 常に機 ίΦ重量の 1 . 2倍の動力が必要で、 5人乗り 1機が 1億 2千万円して高くて簡単 に利用出来ないに対し、 この航空機はプロペラの推力と風 （後流） の力 の 2つを使いへリコブ夕一の半分程の動力で V Τ 0 出来、 巡航は飛行 機のように推力と翼で飛び機体重量の 1 Ζ 4で飛べます。  As described above, according to the present invention, an aircraft capable of V Τ 0 L with a power less than the weight of the fuselage is not only useful for industrial activities such as movement, logistics activities, rescue of life, fire fighting activities, In the event of a social problem such as the Great Hanshin Earthquake or a wildfire in Indonesia, it can be easily solved by using 10,000 aircraft. Helicopter Heichibu Yuichi is VTOL-friendly, but it always requires 1.2 times the power of the ίΦ weight, and one 5-seater aircraft costs 120 million yen and is expensive and easy to use. On the other hand, this aircraft can use two of the propeller thrust and the wind (wake) power to produce V Τ 0 with about half the power of Ricoh in the evening, and cruises with thrust and wings like an airplane. It can fly at 1Ζ4 of the aircraft weight.
V T O Lがへリコブ夕一の半分程の動力で出来、 巡航も 1 / 4以下の 動力でよく、 部品もヘリコプターのように特殊品でなくて標準品でよく 、 主翼の中に人が乗り胴体が不要、 ί吏用動力が半分以下と少なくてよく エンジン等が小さくてよく重量が 2 Ζ 3程と軽く、 積載率がよく、 大量 生産も出来、 機体费は 1 Ζ 2から 1 2 0程も安くなります。  VTOL can be made with about half the power of Helicopter in the evening, cruising can be less than 1/4 of the power, parts can be standard products instead of special products like helicopters, people can ride in the wing and the fuselage No need, power for ministry is less than half, engine is small, weight is about 2 23, light loading capacity is good, mass production is possible, and aircraft 费 is about 1Ζ2 to 120 It will be cheaper.
5入乗りで比較すると、 ヘリコプターは現在機体費は 1機 1億' 2千万 円します力 この航空機はヘリコプターの 1 / 2の 6千万円から将来は 1ノ2 0の 6 0 0万円程と自動車なみになり、 多くの入々が自動車のよ うに簡単に利用出来、 各国数百万機から数千万機も利用され、 阪神大 震災ゃィンドネシァの山火事等の社会問題でも 1万機以上が協力し、 直 ぐに解決出来ます。 Helicopter now costs 100 million'20 million yen for a helicopter It was about 200,000 yen, about 200,000 yen, and many people could use it as easily as a car, and millions to tens of millions of vehicles were used in each country. More than 10,000 aircraft can cooperate and solve social issues such as Indonesian forest fires immediately.
又、 日常生活でも最短時間で移動出来、 生活が充実し、 空のレジャー を楽しむことが出来ます。  Also, you can move in the shortest time in your daily life, enrich your life and enjoy the leisure in the sky.

Claims

請求の範囲 The scope of the claims
[請求頃 1 J 主翼の前及び後ろにプロペラゃジ ッ ト噴射等の推 進器をつけ、 前の推進器では、 機体を前に引き、 かつ、 推進器の後流 により、 主與に揚力を与えるように設けられ、 後の推) 器は、 機 を 持ち上げるとともに、 前の推進力に抗するように機体を後方に引き、 機体を後方斜め上に引くように設けられており、 前の推進器の後流が 主翼の上表面の真中あたりから後緣にかけて剥離を起こし揚力効率を 低下させるのを防ぎ、 大きな揚力を得られるように、 後の推退器の後 流が主翼の後縁に向いていることを特徴とす'る V T O L型の航空機。  [At the time of request 1 J Propeller jet injection and other propellers are installed in front of and behind the main wing, and in the front propulsion unit, the airframe is pulled forward and the wake of the propulsion unit is lifted by the main unit. The rear propeller is provided so as to lift the aircraft, pull the aircraft rearward against the forward propulsion, and pull the aircraft diagonally rearward and upward. In order to prevent the wake behind the thruster from separating from the middle of the upper surface of the main wing to the rear and lowering the lift efficiency, and to obtain a large lift, the wake behind the retraction device is the trailing edge of the wing VTOL-type aircraft characterized by being suitable for
青求項 2 ] 前の推進器の後流が、 主翼の下で拡散するのを防ぐ ように主翼の下の両側方において双胴が設けられ、 前記双胴の間にお いて、 主 翼の後部にフラップが設けられていることを特徴とする請 求項 1に記載の航空機。  Blue seeking 2] A twin fuselage is provided on both sides below the main wing so as to prevent the wake of the previous thruster from spreading under the main wing. The aircraft according to claim 1, wherein a flap is provided at a rear portion.
[請求項 3 ] 離着陸時以外で、 機 ί本が失速速度以上の時、 安定安 全に飛ぶため、 重心位置を主翼の前縁からの距離を変化させるため に、 入が移動したり、 重りを移動させたり、 座席ごと移動したり、 空 気方式で変化させることを特徴とする請求頃し 又は、 2記載の航空 機。  [Claim 3] Except during take-off and landing, when the aircraft is at stall speed or higher, the aircraft moves stably and safely.In order to change the position of the center of gravity from the leading edge of the main wing, the entrance moves or weights. 3. The aircraft according to claim 2, wherein the aircraft is moved, the entire seat is moved, or the air system is changed.
[請求項 4 ] 前記空気方式は、 離着陸時に主翼の上方面から空気 を吸い、 空気の剥離をなく して、 揚力係数を大きく し、 機体の安定を 調節するように、 吸った空気を機 ί本前後から吐出することを特徴とす る請求項 3に記載の航空機。 【請求項 5 j 離着陸時以外で機体速度が失速速度以上の時、 機体 後部の推進軸を前向きに回転して、 大きな推進力にして飛ぶことを特 徴とする請求項 1から 4のいずれかに記載の航空機。 [Claim 4] The air system sucks air from the upper surface of the wing during takeoff and landing, eliminates the separation of air, increases the lift coefficient, and adjusts the stability of the airframe. 4. The aircraft according to claim 3, wherein the jet is discharged from around the time. Claim 5 j Any one of claims 1 to 4, characterized in that when the aircraft speed is higher than the stall speed except during takeoff and landing, the propulsion shaft at the rear of the aircraft rotates forward to fly with a large propulsion force. The aircraft described in.
PCT/JP1998/005666 1998-07-23 1998-12-14 Vtol aircraft WO2000005131A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP24100198A JP2002240797A (en) 1997-02-06 1998-07-23 Vtol type aircraft
JP10/241001 1998-07-23

Publications (1)

Publication Number Publication Date
WO2000005131A1 true WO2000005131A1 (en) 2000-02-03

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Application Number Title Priority Date Filing Date
PCT/JP1998/005666 WO2000005131A1 (en) 1998-07-23 1998-12-14 Vtol aircraft

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9085355B2 (en) 2012-12-07 2015-07-21 Delorean Aerospace, Llc Vertical takeoff and landing aircraft
US10994838B2 (en) 2012-12-07 2021-05-04 Delorean Aerospace, Llc Vertical takeoff and landing aircraft

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3329376A (en) * 1965-09-07 1967-07-04 Paul D Sullivan Short takeoff and landing aircraft
US4358074A (en) * 1979-05-24 1982-11-09 The Boeing Company Propulsion system for V/STOL aircraft
JPH0322282U (en) * 1989-07-14 1991-03-07
JPH1134992A (en) * 1997-07-23 1999-02-09 Takeji Nishimoto Aircraft capable of vtol by kite-flying method

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3329376A (en) * 1965-09-07 1967-07-04 Paul D Sullivan Short takeoff and landing aircraft
US4358074A (en) * 1979-05-24 1982-11-09 The Boeing Company Propulsion system for V/STOL aircraft
JPH0322282U (en) * 1989-07-14 1991-03-07
JPH1134992A (en) * 1997-07-23 1999-02-09 Takeji Nishimoto Aircraft capable of vtol by kite-flying method

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9085355B2 (en) 2012-12-07 2015-07-21 Delorean Aerospace, Llc Vertical takeoff and landing aircraft
US9862486B2 (en) 2012-12-07 2018-01-09 Delorean Aerospace, Llc Vertical takeoff and landing aircraft
US10994838B2 (en) 2012-12-07 2021-05-04 Delorean Aerospace, Llc Vertical takeoff and landing aircraft
US11912404B2 (en) 2012-12-07 2024-02-27 Delorean Aerospace, Llc Vertical takeoff and landing aircraft

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