| 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 | Senkrecht startender und landender Flugkörper | EP88111582.8 | 1988-07-19 | EP0304614A2 | 1989-03-01 | von Kozierowski, Joachim |
Senkrecht startender und landender und in jede Richtung steuerbarer Fliehkraftring in torusähnlicher Form mit mittiger Aufnahme von Transportkapseln für die Fortbewegung in einem beliebigen Medium, bestehend aus übereinander oder ineinander angeordneten Kreisringschalen, die in einem Abstand konzentrisch um eine Mittelachse rotieren, wobei jede Kreisringschale für sich aus, auf einem Kreisring nebeneinander angeordneten, über Separatorring (4) und Lagerringe miteinander verbundenen, Verdichter- (1) und Turbinenschaufeln (2) besteht. und die ein oder mehrere Energieaggregate haben, die die Kreisringschalen antreiben, so daß das umgebende Medium von den Kreisringschalen aufgenommen, beschleunigt und über Düsen (10) ausgestoßen wird, wobei der Fliehkraftring selbst gegenüber der Mittelachse mittels einer elektronisch gesteuerten Bremsanlage (14) an den gegenläufigen Schalen oder über Düsen oder über eine ausladende Drehmomentstütze drehstabil gehalten wird. |
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| 82 | Fall-down preventing device for vertically long body | JP20878899 | 1999-07-23 | JP2001032999A | 2001-02-06 | YAGI MITSUTOSHI |
| PROBLEM TO BE SOLVED: To be brought into contact a vertically long body with a strut with two tangential lines so as to stably hold a vertically long body by providing an attaching member for attaching two or more struts separating from each other on a base plate and for attaching the base plate and the struts freely to dismount, and a fixing member for fixing the vertically long body to the struts. SOLUTION: A fall-down preventing device 1 is provided with a base plate 2, a pair of struts 3 attached to the base plate 2 freely to dismount, an attaching member 4 for attaching the struts 3 to the base plate 2 freely to dismount, and a fixing member 5 for fixing vertically long bodies to the struts 3. Since the vertically long bodies are supported by two struts 3, the vertically long bodies can be held in condition which is brought into contact with the struts 3 with two tangential lines, and the vertically long bodies are stably held so as to prevent fall-down. The device 1 can correspond to vertical long bodies having different diameters, various kinds of the vertical long bodies can be held, and also they can be arranged at a free field regardless of an existence and kinds of a supporting body such as a wall of a building, and a fixing body. COPYRIGHT: (C)2001,JPO | ||||||
| 83 | LANDING ARRESTING SYSTEM FOR VERTICAL TAKE-OFF AND LANDING (VTOL) AERIAL VEHICLES, LANDING AND TAKE-OFF PLATFORM FOR VTOL AERIAL VEHICLES AND VTOL LOCKING MEMBER FOR AERIAL VEHICLES | EP12880637 | 2012-07-05 | EP2870068A4 | 2016-03-09 | CARDELL PER-ERIK; STENBOM KJELL |
| 84 | LANDING ARRESTING SYSTEM FOR VERTICAL TAKE-OFF AND LANDING (VTOL) AERIAL VEHICLES, LANDING AND TAKE-OFF PLATFORM FOR VTOL AERIAL VEHICLES AND VTOL LOCKING MEMBER FOR AERIAL VEHICLES | EP12880637.9 | 2012-07-05 | EP2870068A1 | 2015-05-13 | CARDELL, Per-Erik; STENBOM, Kjell |
| The present invention relates to a landing arresting system for vertical take-off and landing (VTOL) aerial vehicles(1) comprising a landing and take-off platform(6) and at least one VTOL locking member (4) having a projecting portion (32) arranged at a lower portion of the vehicle (1). The landing and take-off platform(6) comprises a plurality of individually displaceable rolls (12),arranged substantially in a horizontal direction, and moveable back and forth, such that the projecting portion (32) of the VTOL locking member (4) can be entered, retained and released between two adjacent rolls (12). The present invention also relates to a landing and take-off platform for VTOL aerial vehicles and a VTOL locking member for aerial vehicles. | ||||||
| 85 | FLUGZEUG MIT DER EIGENSCHAFT ZU SCHWEBEFLUG, SCHNELLEM VORWÄRTSFLUG, GLEITFLUG, KURZSTART, KURZLANDUNG, SENKRECHTSTART UND SENKRECHTLANDUNG | PCT/CH2007/000109 | 2007-03-02 | WO2007098634A1 | 2007-09-07 | POSVA, David |
Flugzeug mit zwei, vorzugsweise vier oder mehr Rotoren (20) in verschliessbaren Tragflächenluken (10). Der Verschliessmechanismus besteht oben aus individuell gekrümmten Elementen auf einem Trägerrollo (40), unten aus Längslamellen (30). Die Rotoren werden jeweils von einem oder mehreren Motoren angetrieben (50). Ein oder mehrere Propeller-/Impellerantriebe sind fest mit dem weit schwenkbaren Höhenruder verbunden (60). Im Schwebeflug sind die Tragflächenluken (10) geöffnet und die Impellerantriebe (60) mit dem Höhenruder weitgehend senkrecht nach unten geschwenkt. Beim Übergang in den Vorwärtsflug wird die grosse Wölbklappe (100) nach unten gestellt und die Propeller-/Impellerantriebe (60) mit dem Höhenruder langsam in die Horizontale geschwenkt. Bei genügender Vorwärtsgeschwindigkeit werden die Tragflächenluken (10) geschlossen, die Rotoren (20) abgestellt und die Wölbklappe (100) wieder etwas hochgefahren. Durch die Lücke zwischen den Flügelspitzen (70) hat der Pilot freie Sicht in alle Flugrichtungen auch bei Tragflächenlukenanteilen vor dem Pilotensitz. Eine Stangenspitze (80) zwischen den Flügelspitzen (70) schützt vor dem einhängen von Kabeln. Beim Ausfall des Rotorensystems im Schwebeflug nahe am Boden wird der Aufprall durch Feststoffraketen (110) gedämpft. |
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| 86 | Vertical take off and landing unmanned aerial vehicle airframe structure | EP09176972.9 | 2009-11-24 | EP2193993A3 | 2013-03-27 | Goossen, Emray |
An unmanned aerial vehicle selectively formed of high strength composite structural part portions and lightweight aerodynamic foam portions to provide a low-cost and lightweight UAV that comports with export, civil airspace, and safety regulations. To further to reduce an overall weight of the UAV, mechanical elements are designed to provide multiple functionalities. Structural elements may be manufactured in same or similar non-specialized processes, and non-structural elements manufactured in same or similar non-specialized processes, reducing overall manufacturing costs. Materials and bonding elements are selected to provide frangibility and yet maintain normal flight structural integrity.
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| 87 | Control device for vertical landing | US52710855 | 1955-08-08 | US2930549A | 1960-03-29 | GUNTHER ERNST |
| 88 | 자동차 트레일러의 1번 차축 시스템을 신설하고 상하가변장치와 랜딩잭을 구성설치한 자동차 트레일러 | KR2019960058492 | 1996-12-27 | KR2019980045352U | 1998-09-25 | 홍순무 |
| 자동차트랙터 1번차축시스템(1)을자동차트레일러응용선택적용하여자동차트레일러 1번차축시스템(12)을설치하되상하로가변되도록상하가변장치(11)를설치하고 A,B양프레임(14)(14')간의중앙부에랜딩잭(8)을설치하고자동차트레일러의조향장치는신 4륜트랙터와연계관련구성하여작동되는구성으로서종래기존트랙터연결트레일러차량의단점을보완하고신 4륜트랙터와연결운행하면서보다더효율성있고주차와연결분리가용이하고적재정량의범위내에서최대의운송효율성과연료소비를절감하고신 4륜트랙터와연결하여운행되는자동차트레일러 1번차축시스템(12)을설치하고상하가변장치(11)와랜딩잭(8)을장착한자동차트레일러이다. | ||||||
| 89 | 관절형 붐 어샘블리를 갖는 단거리 이착륙 및 수직 이착륙 자유 날개 항공기 | KR1019950703027 | 1994-01-21 | KR1019960700173A | 1996-01-19 | 엘버트엘.루탄; 휴즈제이.쉬미틀 |
| 90 | AERODYNAMIC INTEGRATION OF A PAYLOAD CONTAINER WITH A VERTICAL TAKE-OFF AND LANDING AIRCRAFT | EP07872257.6 | 2007-07-19 | EP2046637B1 | 2014-06-04 | ALBER, Mark, R.; STILLE, Brandon, L.; SMILEY, Alfred, Russell |
| 91 | AERODYNAMIC INTEGRATION OF A PAYLOAD CONTAINER WITH A VERTICAL TAKE-OFF AND LANDING AIRCRAFT | EP07872257 | 2007-07-19 | EP2046637A4 | 2013-04-17 | ALBER MARK R; STILLE BRANDON L; SMILEY ALFRED RUSSELL |
| 92 | AERODYNAMIC INTEGRATION OF A PAYLOAD CONTAINER WITH A VERTICAL TAKE-OFF AND LANDING AIRCRAFT | EP07872257.6 | 2007-07-19 | EP2046637A2 | 2009-04-15 | ALBER, Mark, R.; STILLE, Brandon, L.; SMILEY, Alfred, Russell |
| A vertical takeoff and landing (VTOL) rotary-wing aircraft is sized and configured to match a payload container such as a standardized Joint Modular Intermodal Container (JMIC). The aircraft may be an Unmanned Air Vehicle (UAV) that is capable of autonomously engaging and disengaging the container so that the aircraft can pick up and drop off the JMIC with minimum human intervention. | ||||||
| 93 | 垂直離着陸機のトルク推定装置、垂直離着陸機、垂直離着陸機のトルク推定プログラム、及び垂直離着陸機のトルク推定方法 | JP2012077012 | 2012-03-29 | JP5832352B2 | 2015-12-16 | 高崎 徹也 |
| 94 | Aircraft capable of vertical short takeoff and landing | US430432 | 1982-09-30 | US4492353A | 1985-01-08 | Bryan D. Phillips |
| An aircraft capable of vertical short takeoff and landing is shown according to the teachings of the present invention as including four separate engine locations. In its most preferred form, the first and second engines are located on opposite sides of the fuselage of the aircraft and are pivotal about first and second axes which are in a plane perpendicular to the longitudinal axis of the aircraft and which are in front of the center of gravity of the aircraft. The third and fourth engines are located on opposite sides of the fuselage of the aircraft and are pivotal about third and fourth pivot axes which are parallel to the first and second axes of the first and second engines, respectively, but which are behind the center of gravity of the aircraft. The engines are mounted and rotated about their respective pivot axes by a system including a shaft having a first end operatively attached to the engine. The shaft is pivotally mounted to the fuselage of the aircraft by a bearing system including first and second tapered roller bearing members wedged between frusto-conical surfaces formed in a bearing mount, on the shaft, and on a collar removably attached to the shaft. A drive gear is attached to the shaft for rotation by a worm gear driven in turn by actuators such as hydraulic or electric motors. Thus, the engines at all four locations can be simultaneously pivoted about their respective axes. | ||||||
| 95 | AERODYNAMICALLY EFFICIENT LIGHTWEIGHT VERTICAL TAKE-OFF AND LANDING AIRCRAFT WITH PIVOTING ROTORS AND STOWING ROTOR BLADES | EP15765196.9 | 2015-03-18 | EP3119674A2 | 2017-01-25 | BEVIRT, JoeBen; STOLL, Alex |
| An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements and a set of tail mounted rotors for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses different configurations of its wing mounted rotors and propellers to reduce drag in all flight modes. | ||||||
| 96 | Plasma actuators for drag reduction on wings, nacelles and/or fuselage of vertical take-off and landing aircraft | EP11156888.7 | 2006-08-17 | EP2340995A3 | 2012-01-25 | Wood, Tommie; Corke, Thomas C.; Post, Martiqua |
An aircraft includes a surface over which an airflow passes. A plasma actuator (1) is configured to generate a plasma above the surface, the plasma coupling a directed momentum into the air surrounding the surface to reduce separation of the airflow from the surface. A method of reducing separation of an airflow from a surface of an aircraft includes generating a plasma in air surrounding the surface at a position where the airflow would separate from the surface in the absence of the plasma.
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| 97 | AERODYNAMICALLY EFFICIENT LIGHTWEIGHT VERTICAL TAKE-OFF AND LANDING AIRCRAFT WITH PIVOTING ROTORS AND STOWING ROTOR BLADES | EP15765064.9 | 2015-03-18 | EP3119673A2 | 2017-01-25 | BEVIRT, JoeBen; STOLL, Alex |
| An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements and a set of tail mounted rotors for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses different configurations of its wing mounted rotors and propellers to reduce drag in all flight modes. | ||||||
| 98 | PLASMA ACTUATORS FOR DRAG REDUCTION ON WINGS, NACELLES AND/OR FUSELAGE OF VERTICAL TAKE-OFF AND LANDING AIRCRAFT | EP06851273.0 | 2006-08-17 | EP1937552B1 | 2011-06-15 | WOOD, Tommie; CORKE, Thomas, C.; POST, Martiqua |
| An aircraft includes a surface over which an airflow passes. A plasma actuator (1) is configured to generate a plasma above the surface, the plasma coupling a directed momentum into the air surrounding the surface to reduce separation of the airflow from the surface. A method of reducing separation of an airflow from a surface of an aircraft includes generating a plasma in air surrounding the surface at a position where the airflow would separate from the surface in the absence of the plasma. | ||||||
| 99 | PLASMA ACTUATORS FOR DRAG REDUCTION ON WINGS, NACELLES AND/OR FUSELAGE OF VERTICAL TAKE-OFF AND LANDING AIRCRAFT | EP06851273.0 | 2006-08-17 | EP1937552A2 | 2008-07-02 | WOOD, Tommie; CORKE, Thomas, C.; POST, Martiqua |
| An aircraft includes a surface over which an airflow passes. A plasma actuator (1) is configured to generate a plasma above the surface, the plasma coupling a directed momentum into the air surrounding the surface to reduce separation of the airflow from the surface. A method of reducing separation of an airflow from a surface of an aircraft includes generating a plasma in air surrounding the surface at a position where the airflow would separate from the surface in the absence of the plasma. | ||||||
| 100 | 垂直離着陸可能飛行体、飛行体、垂直離着陸可能飛行体のコントローラ、制御方法及び制御プログラムを格納した記録媒体 | PCT/JP2017/039804 | 2017-11-02 | WO2018084261A1 | 2018-05-11 | 鈴木 英男; 鈴木 幸博; 松下 孝太郎; 花田 真樹; 篠原 徹; 新島 典子; 中村 維男 |
機体主部と、平面パターンにおいて機体主部の内部に象限中心を定義し、その象限中心の周りの複数個の象限のそれぞれに独立した同一方向の揚力を発生するように、機体主部を支持するフレーム（１１）と、複数個の象限のそれぞれに、フレーム（１１）に設けられた回転軸によって配置された主プロペラ（３１，３２，３３，３４）と、複数個の象限の中に選択される第１象限において、フレーム（１１）に設けられた回転軸によって配置され、主プロペラと同一回転方向の補助プロペラ（３５，３６，３７，３８）とを備え、第１象限に隣接する他の象限における主プロペラの回転方向は、反対方向である。 |
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