| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 21 | 混合式飞机 | CN96198541.0 | 1996-10-24 | CN1094453C | 2002-11-20 | 汉斯·J·伯恩 |
| 一种混合式飞机有VTOL、R-VTOL和S-STOL功能。飞机有产生升力的机身(1)和四个前后排列的翼段(20)，它们前后排列并可绕其中性轴回转。每个翼段有安装在它上面可回转的旋翼螺旋桨(21)组件，用于提供基本上在水平与垂直之间范围内的推力。机翼和螺旋桨通过外伸架组合在机身上，外伸架设计成有很大的刚度并能将来自机翼和螺旋桨的力分配给机身。机身的形状设计为在气流中产生气动升力并可使构成它所需要的不同弯度的壁板数量减到最少程度。机身设计为由覆盖以半刚性壁板的增压张力框架、有覆盖的下部框架和包覆有头锥的机头构成。覆盖构架的半刚性壁板由气密和耐腐的层压材料制造并借助于连接肋和锁销装置与框架连接。框架由多个弯曲细长串排的分段构成，垂直于机身纵轴线并借助于承扭件连接。电涡轮传动系统可用于驱动飞机。还介绍了一种高级混合式飞机，它有约8至12个高速风扇的替代旋翼螺旋桨。 | ||||||
| 22 | 混合式飞机 | CN02105234.4 | 1996-10-24 | CN1378952A | 2002-11-13 | 汉斯·J·伯恩 |
| 一种混合式飞机有VTOL、R－VTOL和S－STOL功能。飞机有产生升力的机身(1)和四个前后排列的翼段(20),它们前后排列并可绕其中性轴回转。每个翼段有安装在它上面可回转的旋翼螺旋桨(21)组件,用于提供基本上在水平与垂直之间范围内的推力。机翼和螺旋桨通过外伸架组合在机身上,外伸架设计成有很大的刚度并能将来自机翼和螺旋桨的力分配给机身。机身的形状设计为在气流中产生气动升力并可使构成它所需要的不同弯度的壁板数量减到最少程度。机身设计为由覆盖以半刚性壁板的增压张力框架、有覆盖的下部框架和包覆有头锥的机头构成。覆盖构架的半刚性壁板由气密和耐腐的层压材料制造并借助于连接肋和锁销装置与框架连接。框架由多个弯曲细长串排的分段构成,垂直于机身纵轴线并借助于承扭件连接。电涡轮传动系统可用于驱动飞机。还介绍了一种高级混合式飞机,它有约8至12个高速风扇的替代旋翼螺旋桨。 | ||||||
| 23 | 具有大体设计为空气静力浮力体的机身的飞机 | CN98803061.6 | 1998-01-02 | CN1249720A | 2000-04-05 | 赫尔曼·孔克勒 |
| 飞机具有一大体设计成空气静力浮力体的机身以及铰接在机身上、设有螺旋桨并构成驱动装置的联合的浮力－推进装置,它们分别可以在浮力位置和推进位置之间摆动。在浮力位置,各螺旋桨旋转平面大体是水平的,而对各螺旋桨轴加载的相应驱动装置的输出轴大体是竖直的;在推进位置,各螺旋桨旋转平面大体是竖直的,而对各螺旋桨轴加载的相应驱动装置的输出轴大体是水平的。螺旋桨旋转平面可相对于对螺旋桨轴加载的相应驱动装置的输出轴朝四周倾斜。 | ||||||
| 24 | ハイブリッドVTOL機 | JP2016524223 | 2014-06-26 | JP6426165B2 | 2018-11-21 | イーガン,ジェイムズ,シー.; イーガン,ジョール,ディー. |
| 25 | 飛行体 | JP2016016117 | 2016-01-29 | JP6037190B1 | 2016-12-07 | 松本 宏之; 市村 重徳; 五百部 達也; 滝田 瑞樹 |
| 【課題】飛行中に飛行体が人や物と接触した場合であっても、飛行体の安定した飛行を継続させることにある。 【解決手段】プロペラ32と、プロペラ32を駆動するモータ33とをそれぞれが有する複数のロータユニット30と、複数のロータユニット30の上下方向の高さに亘って、複数のロータユニット30の側方を覆う緩衝体と、を備える。 【選択図】図3 |
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| 26 | Configured aircraft to rise and landing vertically | JP2009552616 | 2008-03-10 | JP2010520119A | 2010-06-10 | ファン・ヘルデン、アールベルト・アドリアヌス |
| An aircraft which is configured for vertically ascending and landing, includes at least two wings (2a, 2b, 4a, 51, 4b, 52), a space (2c, 4c) for the generating during operation of climbing power, and an intermediate portion (3), the intermediate portion (3) being provided with thrust motors (6), and the space (2c, 4c) for the generating during operation of climbing power being provided with a quantity of lifting power units (HV). Each lifting power unit includes a first variable volume (V1) for the storage of an amount of relatively light gas which is lighter than atmospheric air, and is configured for the controllable adjustment of an upward force or lifting power by the variable volume taken up by the amount of relatively light gas. | ||||||
| 27 | Basically the aircraft with a fuselage that is designed as an air hydrostatic equation rise body | JP52963998 | 1998-01-02 | JP2001507306A | 2001-06-05 | ヘルマン キュンクレル |
| (57)【要約】 航空機は基本的に空気静力学式上昇体として設計された胴体と、胴体に連接された複合された上昇および推進装置とを有しており、前記複合装置はプロペラを備えて推進ユニットを形成し、かついずれの場合も、それぞれのプロペラ回転面が基本的に水平であり、それぞれのプロペラ・シャフトに作用する、関連する駆動機構の出力シャフトが基本的に垂直である上昇位置と、それぞれのプロペラ回転面が基本的に垂直であり、それぞれのプロペラ・シャフトに作用する、関連する駆動機構の出力シャフトが基本的に水平である推進位置との間で傾動可能である。 プロペラ回転面は関連する駆動機構の、プロペラ・シャフトに作用する出力シャフトに対して全周傾斜可能である。 | ||||||
| 28 | Aircraft having buoyant gas balloon | JP13235193 | 1993-05-12 | JPH06135391A | 1994-05-17 | FUREDERITSUKU FUAAGUSON |
| PURPOSE: To improve the lift and drag obtained by a rotating balloon to obtain good flight characteristics by locating a gondola near the balloon surface and making the gondola top surface matched with the balloon surface. CONSTITUTION: An aircraft comprises a balloon, a central gondola 36, an arm 32 extending therefrom, a shaft 30 for rotatably connecting the balloon with the top end of the arm 32, and a gas turbine engine 40. The balloon has cables 12b forming a series of squares on the balloon surface in addition to peripheral cables 12a, the gondola 36 is disposed very close to the balloon and has a recessed part to the rear of the gondola top behind a standard horizontal shaft 16 to thereby improve the blanking effect. Such constitution restricts the air flow between the balloon and the gondola 36, this reduces the drag caused on the balloon surface while the lift increases with an increase in the balloon rotation speed, thus improving the flight characteristics. COPYRIGHT: (C)1994,JPO | ||||||
| 29 | Radio controlled flying body | JP12541690 | 1990-05-17 | JPH0422386A | 1992-01-27 | KINOSHITA KOICHI |
| PURPOSE: To enhance a reduction in weight and obtain autonomous stability by comprising a ring buoyancy body, a body for receiving two variable speed motors, two servo motors and a control unit, a double reversing propeller, and a radio controller, and setting the center-of-gravity position of the whole body lower than the buoyancy center of the buoyancy body. CONSTITUTION: When the stick of a controller is operated to send a signal to a control unit in a body 7 so that the rotating speeds of propellers 18, 24 rotating in opposite directions are increased or decreased in the state where the rotating speeds of the propellers 18, 24 are conformed to each other to cancel the reaction torques of the propellers 18, 24, a radio control flying body is raised or lowered in a stable state without rotating and tilting. When a slight difference in rotating speed is made between the propellers 18 and 24, a difference is made in the reaction torques given to the body 7 by both the propellers 18, 24, the radio control flying body is gently rotated, and this rotating state can be confirmed by a rear confirming fin 32. At this time, the increase or decrease quantity of rotating speed of the propeller 18 is equal to the decrease or increase quantity of the propeller 24, the radio control flying body is never vertically moved. COPYRIGHT: (C)1992,JPO&Japio | ||||||
| 30 | ＶＥＳＴＡＰＬＡＮ−滑空ヘリスタット | JP2016574187 | 2015-03-30 | JP2017530892A | 2017-10-19 | ボリソウィッチ シュルギン，ニコライ |
| 本発明は、航空の分野に関し、特に、航空機構造に関し、本ハイブリッド航空機は、剛性フレームを有するエアロスタット、ヘリウムを有するガス嚢、懸垂保持システム、及び貨物/旅客キャビンを有する軸受プラットフォームを備える。キャビンは、コントロール、エンジン、電気機器、及び測定デバイスを含み、エアロスタットは、円筒ヒンジによって接続され、固着要素を備える2つのエンベロープからなり、2つのエンベロープの回転を制御し、2つのエンベロープの回転は、エアロスタットを、変化させ、翼の形態で又は開口フェアリングを有するΛ形状の形態で取付けることを可能にし、懸垂保持システムは、剛性でかつ可撓性の接続部を含み、変形され、取付けられることが可能であり、エンジンは、垂直平面内で360°だけ推力ベクトルの方向を変更し、取付けられる能力を持って設置され、デバイスを安定位置に配備し取付けることは、傾斜した硬質大地表面上で、水表面上で、又は垂直構造上で実施される可能性があり、傾斜表面上に配備する場合、軸受プラットフォームは、アンカーに取付けられ、エアロスタットエンベロープは、表面と接触状態になるまで下方に回転する。水上に配備する場合、エンベロープは、エンベロープの一部分が水中に浸漬されるまで下方に回転し、垂直構造上に配備する場合、係留フックは、前エンベロープの端に更に設置され、前記フックはアンカーに取付けられる。【選択図】図1 | ||||||
| 31 | Wing both equity type airplane | JP2009532118 | 2008-08-12 | JP5290976B2 | 2013-09-18 | 政彦 鈴木 |
| Provided is a positive-pressure floating type airplane (10) comprising an airfoil portion (12), left-right fuselages (30A and 30B), a central fuselage (40), an elevator (50) and a rudder (52) disposed at the back of the airfoil portion (12), a thruster (54) disposed at the back of the central fuselage (40), and a horizontal stabilizer (56) disposed at the rear ends of the left-right fuselages (30A and 30B). The individual front ends of the airfoil portion (12), the left-right fuselages (30A and 30B) and the central fuselage (40) are formed into arcuate shapes in longitudinal sections. On the lower side of the airfoil portion (12), a recessed air capture (32) is formed from the front end to the rear end. As a result, the positive-pressure floating type airplane (10) is floated by the reaction from the air at the time when the air to pass the air capture (32) through the airfoil portion (12) is pushed by the thrust of the thruster (54), and is propelled forward by the component of that thrust. | ||||||
| 32 | Hybrid aircraft | JP51615697 | 1996-10-24 | JPH11513635A | 1999-11-24 | ボセ ハンス−ユーゲン |
| A hybrid aircraft having VTOL R-VTOL and S-STOL capabilities having a lifting body hull (1) and four wing sections (20) arranged in tandem which are pivotally moveable about their neutral axis. Each wing section has mounted thereon a pivotal propeller-rotor (21) assembly for providing thrust substantially in a range between horizontal and vertical. The wings and propellers are integrated to the hull by an outrigger designed to be very stiff and to distribute forces from the wings and propellers from the hull. The hull is shaped to provide aerodynamic lift in an airstream and to facilitate construction by minimizing the number of panels of differing curvature required. The hull is formed of a pressure tensioned frame covered with semi-rigid panels, a lower cladding frame and bow and stem cladding nose cones. The semi-rigid panels covering the frame are formed of gas-tight and abrasion resistant laminate material and are connected to the frame by means of an interface rib and latch system. The frame is formed of a plurality of curved elongate segments arranged in series orthogonal to the long axis of the hull and connected by means of torsion members. A turbo-electric drive system can be used to drive the aircraft. An advanced hybrid aircraft is also described having about 8 to 12 high speed fans in place of the propeller-rotors. <IMAGE> | ||||||
| 33 | Aircraft having buoyant gas balloon | JP28515289 | 1989-11-02 | JPH02162196A | 1990-06-21 | FUREDERITSUKU FUAAGUSON |
| PURPOSE: To increase lift and decrease drag as the rotation of a balloon is increased by providing a balloon rotating means generating the Magnus lifting force that the static lifting force of a balloon means is increased by the surface characteristic of the balloon means during the rotation in a forward flight. CONSTITUTION: A balloon is provided with peripheral cables 12a and cables 12b forming a series of squares on the surface of the balloon. When the balloon is inflated by floating gas such as helium, the balloon is slightly inflated between the cables 12a, 12b by the pillow effect, the irregularity of the magnitude improves the Magnus effect and decreases drag. An electric motor fitted to the apex of an arm 32 is rotated, the balloon is rotated around the standard horizontal axis 16, the balloon is advanced by a gas turbine engine 40, and the balloon is moved above the center. The Magnus lift quantity depends on the advancing speed of the balloon, the rotating speed of the balloon, and the irregularities on the surface of the balloon. COPYRIGHT: (C)1990,JPO | ||||||
| 34 | Aircraft with floating gas balloon | JP19194882 | 1982-11-02 | JPS5885795A | 1983-05-23 | FUREDERITSUKU FUAAGUSON |
| 35 | 하이브리드 수직이착륙 운송수단 | KR1020157037252 | 2014-06-26 | KR1020160024363A | 2016-03-04 | 에간,제임스,씨.; 에간,조엘,디. |
| 하이브리드수직이착륙운송수단은유체정역학부력을제공하도록구성된기낭, 기낭에부착되고움직임을통하여동적양력을생성하기위해동체의반대측면들로부터연장되는적어도한쌍의날개들을갖는동체및 각각의날개상에그리고수직이륙또는착륙성능들을제공하기위해서기낭의종축에횡방향에있는축에대하여각각의날개와함께회전하도록구성된추력생성디바이스를갖는다. 이상적으로는, 기낭은저-속도및 대지상에서의안정성을증강시키기위해음(negative)의유체정역학양력을제공한다. | ||||||
| 36 | 정압 부양형 비행기 | KR1020107007783 | 2008-08-12 | KR1020100054158A | 2010-05-24 | 스즈키마사히코 |
| Provided is a positive-pressure floating type airplane comprising an airfoil portion, left-right fuselages (30A and 30B), a central fuselage (40), an elevator (50) and a rudder disposed at the back of the airfoil portion, a thruster disposed at the back of the central fuselage (40), and a horizontal stabilizer (56) disposed at the rear ends of the left-right fuselages (30A and 30B). The individual front ends of the airfoil portion, the left-right fuselages (30A and 30B) and the central fuselage (40) are formed into arcuate shapes in longitudinal sections. On the lower side of the airfoil portion, a recessed air capture (32) is formed from the front end to the rear end. As a result, the positive-pressure floating type airplane is floated by the reaction from the air at the time when the air to pass the air capture (32) through the airfoil portion is pushed by the thrust of the thruster, and is propelled forward by the component of that thrust. | ||||||
| 37 | ハイブリッドＶＴＯＬ機 | JP2016524223 | 2014-06-26 | JP2016526508A | 2016-09-05 | イーガン，ジェイムズ，シー．; イーガン，ジョール，ディー． |
| 静水力学的浮力を与えるように構成された気嚢と、気嚢に取り付けられ、少なくとも一対の翼を有する胴体であって、翼が胴体の両側から延在して動きによって動的揚力を生成する胴体と、各翼に搭載され、各翼とともに気嚢の長手方向軸の側方にある軸の周りに回転して、垂直離着陸の機能を与えるように構成された推力発生装置とを有するハイブリッドVTOL機である。理想的には、気嚢は、低速及び地上での安定性を強化するために負の静水力学的浮力を与える。【選択図】図1 | ||||||
| 38 | Configured aircraft to rise and landing vertically | JP2009552616 | 2008-03-10 | JP5453115B2 | 2014-03-26 | ファン・ヘルデン、アールベルト・アドリアヌス |
| 39 | 正圧浮揚型飛行機 | JP2009532118 | 2008-08-12 | JPWO2009034805A1 | 2010-12-24 | 鈴木 政彦; 政彦 鈴木 |
| 正圧浮揚型飛行機10は、主として翼形状部12と、左及び右側胴部30A、30B、中央胴部40と、翼形状部12の後部に設けられた昇降舵50、方向舵52及び中央胴部40の後部に設けられた推進器54、右及び左側胴部30A、30Bの後端部に設けられた水平尾翼56とを備え、翼形状部12、右及び左側胴部30A、30B、中央胴部40のそれぞれの前端は縦断面において円弧形状とされ、且つ、翼形状部12の下側には、前端から後端に至る凹溝形状の空気捕捉部32が設けられていて、推進器54の推力により翼形状部12を介して空気捕捉部32を通る空気を押したときの空気からの反力により浮上し、推力の分力により前進する。 | ||||||
| 40 | Apparatus for removing harmful gas from atmosphere | JP2009043983 | 2009-02-26 | JP2009220107A | 2009-10-01 | KONIGORSKI DETLEV |
| PROBLEM TO BE SOLVED: To provide an apparatus capable of reducing harmful gases existing in the atmosphere. SOLUTION: The apparatus for removing harmful gases from the atmosphere consists of a platform which is designed to be operated autonomously in the earth's atmosphere and has a housing of a lightweight structure provided with an inlet for sucking the surrounding atmosphere and an outlet for discharging treated products. Various units for extraction and separation of gases and those for storage and treatment of liquid and gaseous products are arranged inside the housing. The energy required to operate an individual unit of cryogenic circulation loops is generated from a solar cell. COPYRIGHT: (C)2010,JPO&INPIT | ||||||
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