| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | FLUGGERÄT MIT EINER MEHRZAHL VON HUB- UND SCHUBROTOREN | EP03711921.1 | 2003-03-05 | EP1483526A1 | 2004-12-08 | Wobben, Aloys |
| The invention relates to an aircraft comprising a number of lifting rotors and propulsion rotors, provided with an electric motor for each rotor and with a power inverter for each motor. The aim of the invention is to provide an aircraft that has a higher load capacity. To this end, connecting bars are provided between the motors. The invention is based on the finding that connecting bars of this type, when they are arranged in the form of a lattice, enable a light yet stabile structure of the aircraft that, correspondingly, can carry heavier loads. | ||||||
| 82 | Hybrid aircraft | EP02075630.0 | 1996-10-24 | EP1211173A3 | 2002-11-27 | Bothe, Hans-Jurgen |
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. |
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| 83 | Hybrid aircraft | EP02075631.8 | 1996-10-24 | EP1209076A3 | 2002-11-27 | Bothe, Hans-Jurgen |
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. |
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| 84 | DEVICE BY A HORIZONTALLY AND VERTICALLY FLYING AIRCRAFT | EP01901605.4 | 2001-01-23 | EP1255672A1 | 2002-11-13 | GLOMSTAD, Geir, O.; HUKKELAS, Thor; OTTERLEI, Ragnvald |
| An arrangement for a horizontally and vertically flying aircraft of the type that for vertical flight has rotors that form a lifting area such as in a helicopter, and where the rotors are retracted within a rotor disc (4) during horizontal flight. The rotors (8) are supported with fixed pitch in the rotor disc (4). The centre point of the lifting area is arranged to be capable of being shifted in an xy plane, or means are provided to be brought at determined points within the lifting area of the rotor disc (4) to break the lifting capabilities in the effective rotor disc for manoeuvring and counteracting differential lift during propulsion of the aircraft in vertical flight and on the transition from vertical to horizontal flight. | ||||||
| 85 | METHOD FOR CONVERTING THE ROTATION OF A SOLID BODY INTO LINEAR TRACTION FORCE ACCORDING TO A DIRECTIONAL UNBALANCE PROCESS, AND DEVICES FOR REALISING THE SAME | EP97927510.4 | 1997-05-23 | EP1213477A1 | 2002-06-12 | Ekhin, Jury Bronislavovich |
The present invention uses the well-known effect of disbalance of a rotating solid body that is wobbling and thus generation vibrations. But this effect converted into such form that the wobbling are always developed in one direction towards the axis and that its pulses are levelled, as result a constant linear propulsion force of high smoothness and efficiency is obtained. This occurs in the following manner: moving masses (2) are placed on the body (1) and while the body (1) is rotating they are forced in turm to move away from the body axis (Ao) and approach back of one complete rotation of the body. The masses move away from the axis occurs under the rotation of the body, while the approach of the masses towards the axis is occurring under the influence of radial centripetal forces. Under this reason there is no occurrence of the mutual neutralisation of forces which are responsible for retreat and approach motions of the masses. Simultaneous action of all centrifugal forces creates in geometrical sum the resultant force which is applied to the body axis. This invention is based on the law of conservation of impulse, Newton's laws, law of conservation and transformation of energy, law of change of body masses centre motion, law of change of angular impulse. In this invention is presented the series of mechanical facilities, which may be used for building new transport systems having properties never reached before, lake those of "flying cars", while using traditional engines, and others. |
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| 86 | HYBRID AIRCRAFT | EP96934255.9 | 1996-10-24 | EP0854821B1 | 2002-05-02 | Bothe, Hans-Jurgen |
| 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. |
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| 87 | HYBRID-STARRLUFTSCHIFFE VON FILIMONOV | EP96935628 | 1996-10-07 | EP0861773A4 | 1999-05-19 | FILIMONOV ALEXANDR IOSIFOVICH |
| The hybrid dirigible craft belongs to the category of flying vehicles which use an air cushion and take off and land at any type of airfield. The aim of the invention is to design an improved dirigible craft capable of taking off from and landing on water and low-load bearing surfaces. To that end the hybrid dirigible craft comprises the following elements: a discoid body (1) with a central passage (2) in which is mounted a flow-permitting body (5) with a rotor (6) on its upper part and secured to the walls by radial partitions (7) which have an aerodynamic profile; the pilot-passenger and cargo compartments (9 and 10 respectively); a propulsion unit with propellers (8), units for landing on an air cushion in the form of an inflatable toroidal bag (11) and wheel-skid supports (12, 13) mounted on the lower surfaces; rotating flaps (3) mounted at the inlet into the central passage (2); control and stabilising elements (4) mounted at the outlet of the central passage (2); outer wing units (14) and a tail assembly with stabiliser (19) and two or more fins (17) mounted on the rear part of the hull; airflow flaps (21) on the rear flaps of the outer wing elements and hull (22); and airflow control surfaces (20) on the stabiliser and outer wing elements. The dirigible craft also has elevons (22) on the stabiliser and a flexible guard element (23) mounted on and underneath the forward part of the toroidal bag (11). It also has gear for taking off from water in the form of gliding surfaces (28) underneath the compartment (9). | ||||||
| 88 | HYBRID AIRCRAFT | EP96934255.0 | 1996-10-24 | EP0854821A2 | 1998-07-29 | Bothe, Hans-Jurgen |
| 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. |
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| 89 | VTOL aircraft utilizing gas flow across wing surfaces for dynamic lift | EP90305237.1 | 1990-05-15 | EP0420382A1 | 1991-04-03 | Hatanaka, Takefumi |
A vertical take-off and landing aircraft (10) has one or more rear-mounted jet engines (20), and one or more jet deflectors (32) shaped for efficiently re-directing the jet flows (52) from the engines (20) to pass over the upper surfaces of the wings (16) of the aircraft (10) when the deflectors (32) are set to an operating position in which they intercept the jet flows (52), thereby producing dynamic lift as a result of a pressure difference between the upper and lower surfaces of the wings. |
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| 90 | MODULAR AND MORPHABLE AIR VEHICLE | PCT/US2011036564 | 2011-05-14 | WO2011146349A3 | 2014-03-27 | PIASECKI JOHN W; FREDERICK PIASECKI W; BRIAN GEIGER; JOHNSON DOUGLAS; PITCAIRN DAVID |
| An unmanned air module includes one or more rotors, engines, a transmission and avionics. Any of several different ground modules may be attached to the air module. The air module may fly with and without the ground module attached. The ground module may be a vehicle ground module and may be manned. The vehicle ground module may transport the attached air module across the ground. The air module may have two rotors, which may be ducted fans, and three different configurations: a tandem rotor configuration, a side-by-side configuration, and a tilted-rotor configuration. | ||||||
| 91 | SPACECRAFT PROPULSION SYSTEM WITH GYROSCOPIC MECHANISM | PCT/TR2008000116 | 2008-09-24 | WO2009041928A2 | 2009-04-02 | TERZIAKIN MEHMET |
| A propulsion method employing gyroscopes with electric motors which are being moved along a closed path in the spacecraft. Rotation axis of the gyroscopes are rotated periodically relative to movement direction so that gyroscopic effect is only obtained during movement in one direction. Thereby a gyroscopic resistance difference is obtained and used as a propulsion force. Another application is to use gyroscopes connected to generators in order to decelerate a spacecraft, transforming the moment created in gyroscope during deceleration into the electrical energy, distribute it to the space as heat transfer by means of radiation through the heat resistant panels. | ||||||
| 92 | 체공시간을 증대시키는 수직이착륙무인기장치와 이의 구현방법과 관련 장치 | KR1020150021362 | 2015-02-12 | KR1020160099216A | 2016-08-22 | 허훈; 조윤현 |
| 본발명은리프팅바디(lifting body) 형태의공력학적특성을갖는동체와양력을생성하는대형주 회전팬, 자세제어와비상시보조추력을제공할수 있는하나이상의보조회전팬, 동체의무게중심근처에배치되는임무장비탑재기구로구성되고, 추가로미익이나동체전 후방에조정면을장착할수 있고, 착륙과이륙시, 상기주 회전팬과상기보조회전팬을작동하여수직으로이착륙을할 수있고, 상기보조회전팬과추가장착가능한조정면을이용하여외부교란에도자세와고도, 위치를유지할수 있고, 상기동체는삼각형이나사각형모양이될 수있는수직이착륙이가능한무인항공기에관한것이다. 이에따라, 더긴 체공시간은더 긴임무시간을가능하게하며, 이를통해 24시간임무에서필요한기체대수를줄일수 있으며, 동일한에너지를사용하면서도더 많은임무를수행할수 있어, 경제성을향상시킨다. 장비교체시간을최소화하여, 임무공백을줄일수 있으며, 임무계획에더 많은유연성을제공한다. | ||||||
| 93 | 수직 이착륙이 가능한 비행체 | KR1020140192798 | 2014-12-30 | KR1020160082563A | 2016-07-08 | 장성호 |
| 본발명은비행체의수직이착륙을위해베르누이의원리를응용하는비행체구조에관한것이다. 본발명은유선형상의날개와비행체의속도에의해발생되는양력의효율도높이는것은물론, 날개가아닌비행체의동체의윗부분을활용해서도고효율의양력을얻어작용반작용원리로는수직이착륙이불가능했던비행체도기존의수직이착륙비행체처럼작동시킬수 있다. | ||||||
| 94 | 무인 비행체 | KR1020140150641 | 2014-10-31 | KR1020160051163A | 2016-05-11 | 유규형 |
| 본발명은무인비행체를개시한다. 본발명은, 베이스부와, 제1 엑튜에이터와상기제1 엑튜에이터의동력에의해회전하는프로펠러를구비하고, 상기베이스부의외측에회동가능하도록설치되는추진부와, 상기베이스부의일면에회전가능하도록설치되는회전플레이트및 상기회전플레이트와상기추진부를연결하는연결암을포함한다. | ||||||
| 95 | 개인용 항공기 | KR1020157001999 | 2012-07-19 | KR1020150023061A | 2015-03-04 | 크루,아이란 |
| 안전하고, 조용하며, 제어가 용이하고, 효율적이며, 소형의 항공기 구성이 복수의 수직 리프트 로터, 종렬 윙 및 전방 추력 프로펠러의 조합을 통해 가능해진다. 전방 및 후방 윙과 조합되는 수직 리프트 로터를 통해, 수직 및 수평 비행시 리프트의 중심과 무게 중심의 균형이 가능해진다. 이러한 윙과 복수의 로터 시스템은 제자리 비행, 전환 비행 또는 순항 비행시 비교적으로 다양한 페이로드 중량에 여유를 줄 수 있으며, 수직 추력에 여유를 줄 수 있다. 상기 추진 시스템은 잠재적인 블레이드 충격으로부터 보호할 수 있고, 승객에게 감각적이고 현실적인 안전성을 향상시켜 제공할 수 있도록 복수의 리프트 로터와 작은 크기의 전방 추력 프로펠러를 사용한다. 복수의 개별적인 로터들을 사용하여 다양성을 제공할 수 있으며, 비행시 기체를 작동시킬 수 없는 단일 지점의 고장 모드를 제거할 수 있다.
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| 96 | 싸리단묽음(#2) | KR1020140001702 | 2014-01-07 | KR1020140019454A | 2014-02-14 | 최종성 |
| The present invention relates to a bundle of bush clover. According to the present invention, an amount of impact applied to each part of the bush clover is maintained when a load is 500 tons. Speeds are increased when a strand of bush clover is cut. The present invention extends the life of an engine by preventing damage to an airplane. | ||||||
| 97 | 개인용 항공기 | KR1020137004144 | 2011-07-19 | KR1020130026506A | 2013-03-13 | 크루,아이란 |
| 안전하고, 조용하며, 제어가 용이하고, 효율적이며, 크기가 작은 항공기 구성이 복수의 수직 리프트 로터, 종렬 윙 및 전방 추진 프로펠러의 조합을 통해 가능하다. 전후방 윙과 조합된 수직 리프트 로터는 수직 및 수평 비행시 리프트의 중심과 무게 중심의 균형을 맞춘다. 이러한 윙과 복수의 로터 시스템은 수직 추력 여분을 제공하면서도, 제자리 비행, 전환 비행 또는 순항 비행시 페이로드 중량을 비교적으로 크게 변경할 수 있다. 상기 추진 시스템은 복수의 리프트 로터와 잠재적인 블레이드 타격으로부터 보호될 수 있을 정도로 작은 크기의 추진 프로펠러를 사용하며, 향상된 반응성과 승객에게 진정한 안정성을 제공한다. 독립적인 복수의 로터를 사용하여 여분을 제공할 수 있고, 비행체가 비행시 전혀 작동할 수 없게 되는 단일 지점 고장 모드를 방지할 수 있다.
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| 98 | 공중 운반선 | KR1020047012971 | 2003-03-05 | KR100612722B1 | 2006-08-17 | 워벤알로이즈 |
| 본 발명은 복수 개의 승강 로터와 추진 로터를 구비하고, 전기 모터와 각각의 모터를 위한 인버터를 구비한 공중 운반선에 관한 것이다. 공중 운반선을 더욱 많은 적재량을 가질 수 있도록 하기 위하여, 모터 사이에 연결 바가 제공된다. 이러한 점에서 본 발명은, 상기 연결 바가 격자 형태로 구성된 경우 가볍지만 안정된 구조를 지닌 공중 운반선을 제공하게 되어서 더 많은 적재 화물을 실을 수 있는 구조를 제공한다. 비행체, 크레인, 공중 운반선. | ||||||
| 99 | 수직이착륙 회전의 항공기용 날개치기 기계장치 | KR1020030045077 | 2003-07-03 | KR1020050003677A | 2005-01-12 | 배한욱 |
| PURPOSE: An ornithopter system for a vertical take-off and landing airplane is provided to supply motive power to the plane by installing a wing front shaft to a rotary cone and a wing rear part to a rotary cylinder and to simplify the structure by removing a sweepforward wing and a backswept wing. CONSTITUTION: In an ornithopter system for a vertical take-off and landing airplane, a wing front shaft(5) is inserted and rotated in a wing front shaft pipe(2) of a rotary cone(1) that rotates about an X-axis. A wing rear ball bearing(6) is inserted and rotated in a wing rear bearing mounting hole(4) of a rotary cylinder(3) that rotates about a Y-axis. The ornithopter system comprises the fuselage, a power source, and a pair of wings(7). When a driving gear coupled with the power source rotates, a driven gear and the rotary cone mounted at both sides of the driven gear rotate and a pair of the wings executes an ornithopter motion. | ||||||
| 100 | VTOL AIRCRAFT WITH A THRUST-TO-WEIGHT RATIO SMALLER THAN 0.1 | EP17020335.0 | 2014-04-17 | EP3263454B1 | 2018-09-26 | Chen, Li Jing |
| An aircraft includes: ailerons (1,2); a turbofan engine (3) comprising a high-temp duct (4) with an openable/ closable propelling nozzle (5), and a low-temp duct (6) with an openable/closable propelling nozzle (7); a high-temp bypass duct (9) comprising an openable/closable inlet (8) connected to the high-temp duct(4), an outer wall(10) and a rectangle outlet(12) with a height-to-width ratio smaller than 0.1; a low-temp bypass duct (15) comprising an openable/closable inlet (14) connected to the low-temp duct (7), an outer wall (16), an inner wall (17) and a rectangle outlet (19) with a height-to-width ratio smaller than 0.1. During vertical take-off/lading, closing the propelling nozzles (5, 7) of turbofan engine (3), and opening the inlets (8,14) of high-temp and low-temp bypass ducts(9,15), low-temp planar air jet (20) is cause to flow over upper surface of the aircraft, thereby generating lift and no air flow over lower one. | ||||||
