| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | EXTREMELY QUIET SHORT TAKE-OFF AND LANDING (STOL) AIRCRAFT | EP16781880.6 | 2016-04-08 | EP3283367A2 | 2018-02-21 | RAHRIG, Kyle; SOMMER, Geoffrey; WAINFAN, Barnaby, S. |
| An extremely quiet short take-off and landing (STOL) aircraft includes: two wings, wherein each wing comprises an engine system; a fuselage structurally connected to each wing; and a ducted fan thruster positioned on the fuselage in an orientation that is rotated relative to the typical orientation on a helicopter. An extremely quiet STOL aircraft includes: two wings, wherein each wing comprises an engine system; a fuselage structurally connected to each wing; channel shrouds surrounding at least one of the engine systems; and a ducted fan thruster positioned on the fuselage. An extremely quiet STOL aircraft includes: two wings, wherein each wing comprises an engine system, the engine system comprising two engine dual packs; a fuselage structurally connected to each wing; and a ducted fan thruster positioned on the fuselage. | ||||||
| 2 | FLUGKÖRPER | EP12714935.9 | 2012-02-08 | EP2673192B1 | 2016-06-01 | Voss, Andreas |
| 3 | FLUGKÖRPER | EP12714935.9 | 2012-02-08 | EP2673192A1 | 2013-12-18 | Voss, Andreas |
| The invention relates to a remote-controlled small flying object comprising at least one lift area (17), comprising at least one pair of propeller drives (12, 13), and comprising a weight element (20), the position of which can be varied to vary the centre of gravity of this small flying object (10) in the longitudinal direction of the small flying object (10). In order to accomplish a more compact and robust design with improved flying characteristics, the lift area (17) of the small flying object (10) is arranged above a plane formed by the axes of rotation of the propeller drives (12, 13) to generate a lifting force for vertical takeoff and/or landing. | ||||||
| 4 | TACTILE PACKAGING FOR CONSUMER GOODS | EP09786046.4 | 2009-07-01 | EP2448832A1 | 2012-05-09 | WEISS, Jacques; MERMOD, Jacques; SUCHET, Virginy |
| Packaging (10) for consumer goods having a discontinuous tactile coating (16) is provided. The discontinuous tactile coating (16) is formed by applying one or more varnishes (18) to the outer surface of the packaging (10) in a pattern comprising a plurality of raised features having a height of at least about 10 microns and a separation of at least about 20 microns. In a preferred embodiment, the discontinuous tactile coating is formed by applying one or more tinted varnishes to the outer surface of the packaging. | ||||||
| 5 | Air vehicle | EP09252585.6 | 2009-11-10 | EP2193992A3 | 2011-11-30 | Gleed, Gerald; Alders, Dean |
An air vehicle comprising only one wing, which is thin and substantially flat, the wing being elongate and preferably diamond-shaped, and a pod removably coupled to the wing for relative rotation about an axis normal to the major surfaces of the wing, the pod bearing a propulsor for the air vehicle. The propulsor may be a propeller with a Custer duct for static lift.
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| 6 | 翼、エアロカー並びに翼を収納及び展開する方法 | JP2015026445 | 2015-02-13 | JP6039714B2 | 2016-12-07 | ナム テウ |
| 7 | 翼、エアロカー並びに翼を収納及び展開する方法 | JP2015026445 | 2015-02-13 | JP2015151128A | 2015-08-24 | ナム テウ |
| 【課題】重量及び複雑さを低減し、各モードにおける操作性に影響を与えず、路面走行モードにおける効率的な操作に資することができ、運転者の後方及び側方の視野を、制限しないエアロカーの翼を提供する。 【解決手段】翼34であって、インボードチャネル54から翼幅方向に延びるアウトボードチャネル56を有した二重チャネル翼を具備し、アウトボードチャネルがアウトボード軸線OP周りに形成され、且つ、インボードチャネルがインボード軸線IP周りに形成される。アウトボード軸線に沿ったアウトボード推進器62と、インボード軸線に沿ったインボード推進器60と、を具備する。アウトボードチャネル56は、アウトボードチャネル56がインボードチャネル54の上に収納されるように、翼弦軸線Wを中心に約180度揺動する。 【選択図】図1 |
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| 8 | Palpable packaging for consumer goods | JP2012600027 | 2009-07-01 | JP3176709U | 2012-07-05 | ヴィルジニー スーシェ; ジャック メルモド; ジャック ワイス |
| 【要約】消費者が容器を手で触る度にある触知感覚を消費者に与える、耐久性のある質感を外面上に有する喫煙物品の容器を提供する。
【解決手段】不連続の触知コーティング１６を有する消費財のためのパッケージング１０が提供される。 不連続の触知コーティング１６は、１又はそれ以上のワニス１８を、少なくとも約１０ミクロンの高さ及び少なくとも約２０ミクロンの間隔を有する複数の隆起した形状構成を含むパターンでパッケージング１０の外面に塗布することによって形成される。 好ましい実施形態において、不連続の触知コーティングは、１又はそれ以上の着色ワニスをパッケージングの外面に塗布することによって形成される。 【選択図】図１ |
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| 9 | JPS591640B2 - | JP1195275 | 1975-01-30 | JPS591640B2 | 1984-01-13 | MAIRON ERU KINGU |
| 10 | JPS50107698A - | JP1195275 | 1975-01-30 | JPS50107698A | 1975-08-25 | |
| 11 | TACTILE PACKAGING FOR SMOKING ARTICLES | EP09786046.4 | 2009-07-01 | EP2448832B1 | 2013-09-04 | WEISS, Jacques; MERMOD, Jacques; SUCHET, Virginy |
| 12 | Air vehicle | EP09252585.6 | 2009-11-10 | EP2193992A2 | 2010-06-09 | Gleed, Gerald; Alders, Dean |
An air vehicle comprising only one wing, which is thin and substantially flat, the wing being elongate and preferably diamond-shaped, and a pod removably coupled to the wing for relative rotation about an axis normal to the major surfaces of the wing, the pod bearing a propulsor for the air vehicle. The propulsor may be a propeller with a Custer duct for static lift.
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| 13 | AN AIRCRAFT INTERNAL WING AND DESIGN | EP03729658 | 2003-01-14 | EP1472136A4 | 2009-05-13 | CARR ROBERT JONATHAN |
| An aircraft designed with three wings located on either side of the fuselage. The forward wing has a downward angle with a curved top and bottom surface. The upper wing is located towards the rear of the aircraft and above the forward wing. The lower wing is located below the upper wing and slightly forward. It is also located to the rear and below of the forward wing. The outer ends of all three wings come into contact at one point. The forward wing uses the Coanda effect to increase the airflow across the top surface of the bottom wing. The aircraft can be designed so that it is large enough to carry people and/or cargo, or to be small enough to be flown as a toy aircraft. The like design can use any type of aircraft engine commonly used today. One embodiment of the aircraft has two turbines, shaft-coupled to a power source, located on either side of the forward end of the fuselage. Each engine has part of its thrust diverted through and directed by a plenum disposed internal of the coanda toward both sides of the fuselage so that an equal amount of thrust flows through the duct and over the wings on either side of the fuselage. This ensures equal lift on the coanda and both wings on either side of the fuselage in the event that one engine malfunctions. | ||||||
| 14 | AN AIRCRAFT INTERNAL WING AND DESIGN | EP03729658.9 | 2003-01-14 | EP1472136A2 | 2004-11-03 | The designation of the inventor has not yet been filed |
| An aircraft designed with three wings located on either side of the fuselage. The forward wing has a downward angle with a curved top and bottom surface. The upper wing is located towards the rear of the aircraft and above the forward wing. The lower wing is located below the upper wing and slightly forward. It is also located to the rear and below of the forward wing. The outer ends of all three wings come into contact at one point. The forward wing uses the Coanda effect to increase the airflow across the top surface of the bottom wing. The aircraft can be designed so that it is large enough to carry people and/or cargo, or to be small enough to be flown as a toy aircraft. The like design can use any type of aircraft engine commonly used today. One embodiment of the aircraft has two turbines, shaft-coupled to a power source, located on either side of the forward end of the fuselage. Each engine has part of its thrust diverted through and directed by a plenum disposed internal of the coanda toward both sides of the fuselage so that an equal amount of thrust flows through the duct and over the wings on either side of the fuselage. This ensures equal lift on the coanda and both wings on either side of the fuselage in the event that one engine malfunctions. | ||||||
| 15 | LIGHTWEIGHT REMOTELY CONTROLLED AIRCRAFT | EP01944161.7 | 2001-05-23 | EP1289830A2 | 2003-03-12 | LIOTTA, Lance A. |
| An aircraft which is designed for remote controlled slow flight, indoor or in a small outdoor yard or field. The aerial lifting body is defined by a series of lightweight planar or thin airfoil surfaces (A1, A2, A3, A4) arranged in a radially symmetrical configuration. Suspended within the cavity (O) formed by the thin airfoil surfaces (A1, A2, A3, A4) is a thrust generating propeller system (C) that is angled upwardly and that can be regulated remotely so as to change the angle of the thrust vector within the cavity (O) for steering. Lifting, stability, turning, and general control of the direction of motion in flight is accomplished without any formal wings, rudder, tail, or control surfaces. | ||||||
| 16 | 소비용 물품을 위한 촉감 포장 | KR1020127002760 | 2009-07-01 | KR101362593B1 | 2014-02-12 | 바이스,쟈크; 메르모드,쟈크; 서쳇,비르기니 |
| 불연속적인 촉감 코팅(16)을 구비하는 소비용 물품을 위한 포장이 제공되어 있다. 상기 불연속적인 촉감 코팅(16)은, 약 10미크론 이상의 높이와 약 20미크론 이상의 간격을 가지는 다수의 상승된 구성을 구비하는 패턴으로 포장의 외부면에 한 번 이상의 니스(18)를 도포함으로써 형성된다. 바람직한 실시예에서, 상기 불연속적인 촉감 코팅은 포장의 외부면에 한 번 이상의 색조 니스를 도포함으로써 형성된다.
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| 17 | 소비용 물품을 위한 촉감 포장 | KR1020127002760 | 2009-07-01 | KR1020120046214A | 2012-05-09 | 바이스,쟈크; 메르모드,쟈크; 서쳇,비르기니 |
| 불연속적인 촉감 코팅(16)을 구비하는 소비용 물품을 위한 포장이 제공되어 있다. 상기 불연속적인 촉감 코팅(16)은, 약 10미크론 이상의 높이와 약 20미크론 이상의 간격을 가지는 다수의 상승된 구성을 구비하는 패턴으로 포장의 외부면에 한 번 이상의 니스(18)를 도포함으로써 형성된다. 바람직한 실시예에서, 상기 불연속적인 촉감 코팅은 포장의 외부면에 한 번 이상의 색조 니스를 도포함으로써 형성된다.
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| 18 | CONFIGURATION FOR VERTICAL TAKE-OFF AND LANDING SYSTEM FOR AERIAL VEHICLES | US16020802 | 2018-06-27 | US20180305007A1 | 2018-10-25 | Andrei Evulet |
| A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tail conduit is fluidly coupled to the generator. First and second fore ejectors are coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element includes a closed wing having a leading edge and a trailing edge. The leading and trailing edges of the closed wing define an interior region. The at least one propulsion device is at least partially disposed within the interior region. | ||||||
| 19 | Semi-open fluid jet VTOL aircraft | US14099929 | 2013-12-07 | US09517840B2 | 2016-12-13 | Bogdan Tudor Bucheru |
| The herein invention is presenting a lift generating method based on a semi-open fluid jet flowing in a closed circuit around a lifting airfoil. A VTOL aircraft with maximized pay load room and car-like shape is the preferred embodiment of the invention. The herein aircraft uses no wings, exposed propellers, hot gas jets or other high injury risk means for propulsion and lift, and it can be driven by ordinary skilled people. Furthermore the aircraft has a small footprint and can land, take off and even cruise on water in one of the preferred embodiments. | ||||||
| 20 | EXTREMELY QUIET SHORT TAKE-OFF AND LANDING (STOL) AIRCRAFT | US14687277 | 2015-04-15 | US20160318606A1 | 2016-11-03 | Kyle RAHRIG; Geoffrey SOMMER; Barnaby S. WAINFAN |
| An extremely quiet short take-off and landing (STOL) aircraft includes: two wings, wherein each wing comprises an engine system; a fuselage structurally connected to each wing; and a ducted fan thruster positioned on the fuselage in an orientation that is rotated relative to the typical orientation on a helicopter. An extremely quiet STOL aircraft includes: two wings, wherein each wing comprises an engine system; a fuselage structurally connected to each wing; channel shrouds surrounding at least one of the engine systems; and a ducted fan thruster positioned on the fuselage. An extremely quiet STOL aircraft includes: two wings, wherein each wing comprises an engine system, the engine system comprising two engine dual packs; a fuselage structurally connected to each wing; and a ducted fan thruster positioned on the fuselage. | ||||||
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