| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 41 | Vertical lift aircraft | JP9814693 | 1993-04-23 | JPH0624391A | 1994-02-01 | RICHIYAADO EICHI JIERONKA |
| PURPOSE: To obtain a remarkable ground effect by rotating a first driving ring means together with a first belt means and rotating the first belt means in response to the rotation of the first roller driving means. CONSTITUTION: A driving ring 43 is driven by an inside belt 52. The inside belt 52 has a feature such as a spring, abuts on the driving ring 43 due to this feature and rotates together with the ring. The belt 52 is rotated by a pair of rollers 53 to rotate the driving ring 43 together with blades 42. On a tubular member 50, a spacer 98 is mounted along its entire length except the part of a frame 23. The spacer 98 decreases air flows around the outer sides of outer rings 44 and 44', so that the efficiency of a rotor system is increased. | ||||||
| 42 | Aircraft having a pair of rotors rotating in opposite direction | JP10434190 | 1990-04-19 | JPH0367799A | 1991-03-22 | FURANTSU BUTSUHIYAA |
| PURPOSE: To obtain an aircraft possible in hovering and horizontal flight by providing a pair of coaxial rotors rotating in reverse directions with each other in a disklike housing arranging an engine and a cabin at the center, and many adjustable air guiding means in the air flow of the rotors. CONSTITUTION: This aircraft has a flat and circular housing 1 having a pair of coaxial rotors 2 and 3 tuning in reverse directions at an equivalent speed, and the housing 1 has a wing portion, for generating aerodynamic lift during flight in a horizontal direction, in the expanded portion in the longitudinal direction of the housing 1. An engine 8 and a cabin 9 for crew are arranged at the center portion of the gravity of the aircraft, and the rotors 2 and 3 are rotated by the engine 8. The respective rotors 2 and 3 are equipped with three vanes fitted to a drive ring 12 at an angle of 120°, and an air flow generated by the rotation of the rotors 2 and 3 is blown off downward via an adjustable air guiding means 16 provided on an air outlet divided into many sectors. COPYRIGHT: (C)1991,JPO | ||||||
| 43 | Annular moving body | JP20799788 | 1988-08-22 | JPS6470297A | 1989-03-15 | YOAHIMU FUON KOTSUIROFUSUKI |
| PURPOSE: To provide a ring type moving body as a carriage for passengers or objects by installing blades in a plurality of sets adjoining at a certain spacing on the peripheral edge of a circle centering on a center shaft, and forming each set of blades from one or two sets of compressor blades in straight form or curved relative to the vertical axis and one set of turbine blades. CONSTITUTION: Compressor blades 1 perpendicular to the center line of a centrifugal force ring work in cooperation with turbine blades 2 installed at the peripheral edge parallel with the center line and also a common separator ring 4 and form a circular ring shell having bearing rings 3 and 4 on the peripheral edge of the circle centering on the center line of the centrifugal force ring. The medium led by the turbine blades 2 is spouted from an adjusting nozzle 7 positioned in the rear. Thus the centrifugal force ring is moved in the selected direction by the reaction force together with a capsule 10 hitched in the center replaceably. The lower part of the casing of centrifugal force ring does not admit permeation of the medium. | ||||||
| 44 | 덕트 구조를 가지는 무인 비행 장치 | KR1020170030977 | 2017-03-13 | KR1020180104362A | 2018-09-21 | |
| 무인비행장치가제공된다. 보다상세하게는양력을증가시키는복수의덕트영역을가지는무인비행장치가개시된다. 개시되는실시예중 일부는벨 마우스형상인유입구영역을통해공기를유입하여양력을증가시키는덕트영역을가지는무인비행장치가제공된다. 이밖의다른실시예가가능하다. | ||||||
| 45 | 접시형 비행체 | KR1020040078977 | 2004-10-05 | KR1020060030187A | 2006-04-10 | 김이섭 |
| 본 고안 발명은 중심부를 향해 갈수록 좁게 형성된 나선으로 형성된 공기통로를 통해 공기팬이 공기를 흡입하며 나선형으로 형성된 공기통로를 지나는 공기의 가속진행시 발생되는 저기압과 가속된 공기가 갖는 에너지를 이용해 부상하며 나선형으로 형성된 공기통로에 대기압이 밀려들때 발생하는 회전력을 조절하므로서 추력을 얻는 접시형비행체에 관한 고안발명이다. 대기압,회전체 공기팬,접시,비행체 | ||||||
| 46 | 揚力発生装置 | JP2015540232 | 2013-09-26 | JP2016502013A | 2016-01-21 | ラファエレ アルテリオ，アンジェロ |
| 【構成】本発明は航空機用揚力発生装置であり、この装置は回転軸(4)を中心にして回転可能であり、そして複数の半径方向トラック(10)を有するロータ(2?、2??)であって、複数の半径方向トラックにおいて上記ロータの回転開始後、質量体(15)が上記トラックに沿って上記ロータの周囲に向かって遠心力によって並進移動するように上記質量体(15)が滑り配置するロータ(2?、2??)、および上記ロータの回転時、上記トラックにそって上記ロータの外部に向かって投射される上記質量体がステータ(3)の形状(18)に追従するように拘束された、上記ロータに対して配置されたステータ(3)を有し、上記ロータの回転時、上記半径方向トラック(10)に沿って往復動する上記ロータの上記回転軸(4)に対する各質量体(15)の距離が変化して、上記質量体の少なくとも第1部分が、上記回転軸(4)から(d1)の距離に位置するように各質量体が変化し、この距離(d1)が上記質量体の少なくとも第2部分によって占められる距離(d2)より大きく、所定の方向にそって遠心力(F)の差分(Δ)を作り出すように上記ステータの形状(18)を構成する。【選択図】図6 | ||||||
| 47 | Wingless hovering of ultra-small airplane | JP2009523018 | 2007-07-31 | JP5220742B2 | 2013-06-26 | サブラタ ロイ |
| Embodiments of the subject invention relate to an air vehicle and a power source. Embodiments can operate at reasonable power levels for hovering and withstanding expected wind gusts. Embodiments can have a diameter less than 15 cm. Embodiments can have one or more smooth (continuous curvature) surface and can be operated using electromagnetic and electrohydrodynamic principles. The wingless design of specific embodiments can allow operation with no rotating or moving components. Additional embodiments can allow active response to the surrounding flow conditions. The issue of low lift to drag ratio and degradation of airfoil efficiency due to the inability of laminar boundary layers attachment can also be significantly reduced, or eliminated. The electromagnetic force can be generated by applying a pulsed (alternating/rf) voltage between a set of grounded and powered electrodes separated by a polymer insulator, dielectric, or other material with insulating properties. | ||||||
| 48 | Wingless hovering of ultra-small airplane | JP2009523018 | 2007-07-31 | JP2009545487A | 2009-12-24 | サブラタ ロイ |
| 本発明の態様は、無翼ホバリング超小型飛行機（WHOMAV）およびその電源ユニット（PSU）に関する。 態様は、ホバリングし、予想される突風に耐える適正な電力レベルで動作し得る。 本発明の態様は、15cm未満の直径を有し得る。 態様は、一つまたは複数の滑らかな（連続的な曲率の）表面を有してもよく、電磁的および電気流体力学的原理を用いて動作されてもよい。 具体的な態様の無翼設計により、回転成分または移動成分のない動作が可能となる。 さらなる態様は、周囲の流れ状態に能動的に対応することができる。 層流境界層付着が不可能であることに起因する揚抗比の低下および翼効率低下の問題はまた、著しく低減されるか、または排除され得る。 電磁力は、ポリマー絶縁体、誘電体、または絶縁特性を有するその他の材料によって分離された一組の接地電極と電源電極との間にパルス（交流/rf）電圧を印加することによって発生し得る。
|
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| 49 | Flight equipment | JP2004540701 | 2003-09-25 | JP2006515542A | 2006-06-01 | ヴァゲルズ、ディーター |
| ここに開示されているのは飛行装置である。 当該飛行装置は、垂直方向に離陸することができ、かつ少なくともホール（１００、２００）内を自由に飛行するために一人または数人の人間を収容することができる、少なくとも一台の飛行ユニット（１０）から構成され、飛行ユニット（１０）がホール（１００、２００、３００）から出るのを前記ホールの境界（２、３、４、５、６）が防止している。 | ||||||
| 50 | Vertical rise type aircraft | JP9814693 | 1993-04-23 | JP3370725B2 | 2003-01-27 | リチヤード・エイチ・ジエロンカ |
| 51 | Thrust flotation | JP52391398 | 1997-11-18 | JP2001504773A | 2001-04-10 | イー． スミス，ボイド; シー． ビンセント，マービン |
| (57)【要約】 動力を受ける地上の乗物及び宇宙船のためのスラスト浮揚と呼ばれる推進及び浮揚の技術及び方法。 推進及び浮揚の機構は、半径方向及び外側に突出する複数の主ロータアーム（４）を有する垂直軸回りに回転する主ロータ（５）を具備し、前記主ロータアームの端部は、前記主ロータアームに対して垂直な軸回りに回転するディスクロータ（２）である。 ボブロータ及びプロップロータは、リフトロータとして使用され、主ロータの水平面に対して垂直である主ロータの半径方向及び垂直面に対して角度を付けられ、水平な乗物の運動のためのスラストを誘起するか、又はスラストを非対称的に誘起する。 | ||||||
| 52 | Airborne object | JP51703797 | 1996-10-23 | JPH11514951A | 1999-12-21 | シィール・ヨハネス |
| (57)【要約】 中心軸線（３）に設けたエンジン駆動のプロペラ（５）と、積載荷重容器（６）を備えた、回転モーメントつり合い式飛行物体（１）において、飛行物体は、安定した姿勢でかつ簡単な操縦手段で、積載荷重を運ぶことができる解決策を提供すべきである。 これは、駆動エンジン（４）によって駆動される中央のプロペラ（５）と、エンジン（４）自体およびまたはこのエンジンに設けられた回転モーメントつり合い手段とが、反対向きに相対回転可能に支承され、これら全部が積載荷重容器と相対的に回転可能に支承されていることによって達成される。 | ||||||
| 53 | Aircraft | JP1326793 | 1993-01-29 | JPH05262295A | 1993-10-12 | Franz Bucher; ブーヒャー フランツ |
| PURPOSE: To provide an aircraft which allows, a driven forward flight at high velocities, utilizing the aerodynamic lift generated by a round air foil, as well as a controlled hovering flight. CONSTITUTION: An aircraft is arranged in a housing 2 and is provided with a rotor generating a lift exceeding the weight of the aircraft. The housing 2 is essentially shaped as a round air foil. A means of guiding air is provided in a rotor zone for controlling the air stream generated by the rotor, by means of which the position of the aircraft can be controlled in hovering flight. The aircraft can be moved into a gliding flight from a hovering flight. On the transition between the hovering flight and the gliding flight, rear wings 8, 8' and stabilizing wings 11, 11' are provided so as to generate controllability dynamically. The rear wings 8, 8' and the stabilizing wings 11, 11' are arranged on the side or inside of the housing of the outside a zone defined by the air stream of the rotor. For the gliding flight, the aircraft is driven by propeller 5 and is followed the round air foil for the lift. | ||||||
| 54 | JPH05501095A - | JP50859091 | 1991-04-03 | JPH05501095A | 1993-03-04 | |
| 55 | JPH043360B2 - | JP50245984 | 1984-06-12 | JPH043360B2 | 1992-01-22 | |
| 56 | JPS62500016A - | JP50044485 | 1984-12-31 | JPS62500016A | 1987-01-08 | |
| 57 | Sweep-back rotary wing with upper wing | JP702184 | 1984-01-20 | JPS60153401A | 1985-08-12 | TSUDA MASARU |
| PURPOSE:To make a rotary wind for an aircraft compact by providing a wing extending in the direction of revolution along the upper surface of a disc the surface of which droops from the shaft center in the centrifugal direction and sending air into the space between the wing and the upper surface of the disc so as to obtain lift. CONSTITUTION:A rotary disc 2, which is a vital part of a vertical take off and landing plane 1, is formed in such a way that the surface of it droops from a rotary shaft center in the centrifugal direction. On the upper surface of the disc 2, the predetermined number of wing grooves are formed in a spiral form in the centrifugal direction and also in the backward direction with respect to the direction of revolution. An upper wing 7, which extends in the direction of revolution from the upper end brim with respect to the direction of revolution, is provided so that lift can be obtained by sending air into a space surrounded by the rising wall 8 of the wing groove, the upper wing 7, and the upper surface of the disc 2. With this contrivance, a rotary wing can be formed into a compact shape. | ||||||
| 58 | Intake propulsion apparatus and aeroplane availing thereof | JP9470077 | 1977-08-09 | JPS5320297A | 1978-02-24 | ARUFUREDO BIZARI |
| 59 | 공기추진 차량 | KR1020157009480 | 2013-09-19 | KR1020150064083A | 2015-06-10 | 마하잔마헤시다타트라이 |
| 본발명에서는공기-추진차량이개시되었다. 공기-추진차량은기부와기부상에설치된거꿀접시모양의본체를포함한다. 다수의구멍세트들은기부와접시모양의본체상의다수의예정된위치들에한정된다. 다수의공기-이동장치는전진및 후진동작을위한공수력을제공하고기부상에서의차량의수평축선회를제공하기위해예정된구멍세트들을거쳐공기를흡입하고다른예정된구멍세트들을거쳐공기를강제배출하도록구성된다. 다수의덕트들은매개의구멍세트의매 구멍들에공기-이동장치를작동상연결하기위해적응되었으며엔진은공기-이동장치를작동시키기위해결합되었다. | ||||||
| 60 | 원반형 회전익 | KR1020087006633 | 2006-02-21 | KR1020080037097A | 2008-04-29 | 보지우크드미트루 |
| A flying discoidal rotorcraft is equipped with a double counter rotated pulsed DC electric linear-toroidal electric motor-generator combined with a magnetically levitated suspension of the rotorcraft body over the propulsion assembly. The inner and outer rims are made up of electro-active-magnetic levitation and guidance pilot electromagnets as the fixed portion of the stator's assembly and electrokinetic motor-generator and also the attached part of the craft's body. The mobile portion is double independent counter rotated ferromagnetic cores, wherein rotors of the electrokinetic motor-generator have three main components: electromagnets or electromagnets including in their functions external and internal electromagnetic and guidance electromagnets and energy collector and inductor; electric motor-generator electromagnet coils; and a ring propeller. | ||||||
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