| 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 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT | EP15819516 | 2015-08-14 | EP3168147A4 | 2017-12-13 | NOROIAN GEVORG SEREZHAEVICH |
| The invention relates to aviation technology, specifically to vertical take-off and landing aircraft. The vertical take-off and landing aircraft comprises two turbines, the lower of which is of plate-like shape, and the upper is of flat or plate-like shape. Each turbine comprises a reactive power plant. The body of each turbine is mounted on a metallic disc connected to a vertical shaft of the aircraft, and is equipped with vanes. The vanes are mounted such that the position thereof can be changed. The aircraft can comprise intermediate turbines which are mounted between the upper and lower turbine and are flat or plate-like. The reactive power plant of each turbine comprises an air engine and receivers which are connected to a compressor. The body of each turbine is metallic and comprises two rings, one of which is connected to the disc, and also radial struts which are mounted along the perimeter of the turbine body and are connected to the rings and vanes. The vanes are mounted in a single row along the perimeter of the body or are arranged in a single tier. The result is an increase in the reliability and economy of the aircraft, and the possibility of the latter moving vertically, horizontally or at any inclination. | ||||||
| 83 | A DEVICE FOR THE GENERATION OF LIFT | EP13801792.6 | 2013-09-26 | EP2917103A1 | 2015-09-16 | Alterio, Angelo Raffaele |
| The present invention refers to a device (1) for the generation of lift and comprising: - A rotor (2', 2'') rotating around a rotation axis (4), the rotor comprising a plurality of radial tracks (10) inside of which masses (15) are slidingly arranged so that, following the set in rotation of the rotor, said masses translate by centrifugal force along said tracks towards the periphery of the rotor; - A stator (3) arranged with respect to the rotor in such a way that, during the rotation of the rotor, the masses projected along the tracks towards the external part of the rotor are bound to follow a profile (18) of the stator (3); - And wherein the profile (18) of the stator is such that each mass (15), during the rotation of the rotor, varies its distance with respect to the rotation axis (4) of the rotor reciprocating along the radial track (10) in such a way that at least a first part of the masses is found at a distance (dl) from the rotation axis (4) that is greater with respect to at least a second part of masses so as to create a difference (Δ) of centrifugal force (F) along a direction. | ||||||
| 84 | STABILIZING POWER SOURCE FOR A VEHICLE | EP06814049 | 2006-09-01 | EP1942846A4 | 2014-09-10 | BASTIAN WILLIAM ALLEN II; SOBOTA ELIZABETH |
| 85 | WINGLESS HOVERING OF MICRO AIR VEHICLE | EP07813600.9 | 2007-07-31 | EP2046640A1 | 2009-04-15 | ROY, Subrata |
| Embodiments of the subject invention relate to a Wingless Hovering Micro Air Vehicle (WHOMAV) and its Power Source Unit (PSU). Embodiments can operate at reasonable power levels for hovering and withstanding expected wind gusts. Embodiments of the subject invention 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. | ||||||
| 86 | METHOD OF STEERING AIRCRAFT BY MOVING THE STAGNATION POINT AND AIRCRAFT USING THE METHOD | EP04742159.9 | 2004-07-01 | EP1651516A1 | 2006-05-03 | KIRJAVAINEN, Kari |
| An aircraft which comprises means providing air circulation and directing said circulation along a housing. Different operational stages of the aircraft such as take off and level flight are achieved by using the same functionally interconnected means. The circulation is achieved by fan means that allow adjusting the blow direction and the blowing force of the flow. A stagnation point (SP) associated with the circulation is also formed if necessary below the housing and the aircraft can be steered by controlling the circulation and the position of the stagnation point (SP). | ||||||
| 87 | FLUGEINRICHTUNG | EP03748086.0 | 2003-09-25 | EP1549405A2 | 2005-07-06 | Wagels, Dieter |
| Disclosed is a flying device comprising at least one flying unit (10) that can accommodate one or fewer persons, is able to take off in a vertical direction, and is used for flying freely within at least one hall (100), the limitations (2, 3, 4, 5, 6) of which prevent a flying unit (10) from leaving the hall (100). The flying unit (2) can be embodied as a flying disk that is provided with a platform (7). A space for one person is provided in the middle of said platform (7) while an arrangement of a lifting set (10', 10', ...) is disposed thereupon. | ||||||
| 88 | Lift generating means for aircraft | EP02250423.7 | 2002-01-22 | EP1247737B1 | 2004-06-09 | Sanders, Albert Owen |
| 89 | ELECTRODYNAMIC FIELD GENERATOR | EP01952736.5 | 2001-07-11 | EP1312152A1 | 2003-05-21 | Tomion, Mark R. |
| This device is a brushless high-voltage electrical generator for producing a high energy external electrodynamic field or continuous quasi-coherent DC corona or arcdischarge of uniformed current density which completely encloses the machine's conductive housing (1). This housing is divided into distinct electrical sections (3-5) and contains a flat conductive rotor (6) electrically links separate negative (3) and positive (5) housing sections and upon which a plurality of toroidal generating coils (35, 40, 56) are rotatably mounted. Circular arrays of stationary permanent magnets (34, 39, 55) are affixed within the housing which induce a constant DC voltage within said coils upon their rotation. The primary voltage generated is electrostatically impressed across the rotor such that great quantities of electronic charge may be transported between the opposite polarity sections (3-5) of the housing, in such a manner that a much higher secondary voltage is caused to appear across interposed neutral sections thereof, and the resulting external breakdown current once initiated is independent of the generating coils'ampacity. Ancillary mechanical, electrical, and/or electronic features may be attached upon or within the housing to aid in harnessing and controlling the useful effects associated with the external dynamic electric field produced by the device. | ||||||
| 90 | FLYING DISK SHAPED FLYING/SPACE VEHICLE WITH THE USE OF A NEW TECHNIC OF THRUST THROUGH THE ROLLING OF A WHEEL | EP01958261.8 | 2001-08-07 | EP1307655A1 | 2003-05-07 | Hatzistelios, Nikolaos C. |
| This invention called airwheel, concerns of a flying disk shaped flying/space vehicle with the use of a new technic of thrust through the rolling of a wheel. If we exercise a force from a fixed point on the edge of a turning wheel (fixed related to the main body of the vehicle) and the direction of the force is opposite to the direction of the linear speed of the edge, then we will simulate the friction force between the turning wheel of a car and the road which forces the rolling of the car wheel and not just the revolving of it. The airwheel uses to roll (fly) a wheel named in the invention rolling wheel (b) and it embraces the main body (a) of the airwheel as well as an other wheel (Angular Momentum Maintenance Wheel (c)) which turns the other way around to maintain the angular momentum. The airwheel uses nozzles (k) to manoeuvre. Airwheel ingests atmospheric air to fly and avoids/standsup against air pockets using gas saved in a cylindric tank in it which diverts gas under great pressure to the nozzles. For the interplanetary flight airwheel uses the magnetic fields of the magnetosphere, magnetotail and the magnetic fields of solar wind. It comprises T-shaped telescopic devices which on the upper side of the 'T' contain couples of superconductor bobbins. | ||||||
| 91 | 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. | ||||||
| 92 | AEROSTAT LIBRE A ROTATION PERMANENTE MOBILE EN TRANSLATION RADIALE PAR RAPPORT A L'AIR ATMOSPHERIQUE | EP99907677.1 | 1999-03-10 | EP1062153B1 | 2002-10-23 | LAFUMA, Pierre; VARGAS, André; EVRARD, Jean, François, Joseph; MERCIER, Flavien, Michel, François |
| 93 | 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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| 94 | AEROSTAT LIBRE A ROTATION PERMANENTE MOBILE EN TRANSLATION RADIALE PAR RAPPORT A L'AIR ATMOSPHERIQUE | EP99907677.1 | 1999-03-10 | EP1062153A1 | 2000-12-27 | LAFUMA, Pierre; VARGAS, André; EVRARD, Jean, François, Joseph; MERCIER, Flavien, Michel, François |
| The invention concerns a free lighter-than-air aerostat comprising a structure (1, 3, 4, 5) symmetrical relative to a main axis (2), at least one main sealed pressurised chamber (16), one or several particle emitting thrusters (8), adapted to drive the aerostat in rotation in one direction about the main axis (2), one or several moving flaps (9) adapted to be set either in an active state wherein they brake the aerostat rotation, or in an inoperative state wherein they offer no substantial resistance to the aerostat rotation, and on-board control means (19) adapted to control the thrusters (8) and the flaps (9) to drive the aerostat in permanent rotation about the main axis (2), and in translation perpendicular to the main axis (2). | ||||||
| 95 | THRUST LEVITATION | EP97949538.0 | 1997-11-18 | EP0939726A1 | 1999-09-08 | SMITH, Boyd, E.; VINCENT, Mervin, C. |
| A propulsion and levitation technology named thrust levitation and methods and arrangements for inducing levitation for purposes such as powering terrestrial vehicles and spacecraft. A propulsion and levitation mechanism comprises a main rotor (5) spinning about a vertical axis having plural radial and outwardly projecting main rotor arms (4), at the end of which is a disk (2) spinning about a horizontal axis to the main rotor arm. Bob rotors and prop rotors may also be used as the lifting rotors and may be angled out of the main rotor radial and vertical plane that is perpendicular to the horizontal plane of the main rotor to induce thrust for horizontal vehicular motion or to induce thrust asymmetrically. | ||||||
| 96 | FLUGKÖRPER | EP96934787.1 | 1996-10-23 | EP0857139B1 | 1999-04-07 | Schier, Johannes |
| The invention concerns an aircraft (1) which has balanced torque and comprises a useful load container (6) and a propeller (5) which is disposed in a central axis (3) and is driven by a drive motor (4). The object of the invention is to provide an aircraft which, in a stable flying attitude and with simple control means, can convey useful loads. This object is achieved in that the central propeller (5) and, relative thereto, the motor (4) itself and/or a torque-balancing means disposed thereon are mounted so as to be rotatable in opposite senses and so as to be together rotatable relative to the useful load container. | ||||||
| 97 | Fluggerät mit einem gegensinnig drehenden Rotorpaar | EP90106212.5 | 1990-03-31 | EP0393410B1 | 1994-05-25 | Bucher, Franz |
| 98 | Fluggerät | EP92122020.8 | 1992-12-25 | EP0553490A1 | 1993-08-04 | Bucher, Franz |
Das Fluggerät besitzt einen angetriebenen, in einem Gehäuse (2) liegend angeordneten Rotor, mittels welchem eine Auftriebskraft erzeugbar ist, die das Gewicht des Fluggerätes übersteigt. Das Gehäuse ist im wesentlichen als Rundflügel ausgebildet. Im Bereich des Rotors sind Luftführungsmittel vorgesehen zur Beeinflussung des Rotorstrahls, womit die Lage und die Bewegungen im Schwebeflug steuerbar sind. Das Fluggerät kann vom Schwebeflug in einen angetriebenen Gleitflug übergehen. Für diesen Uebergang sowie den Gleitflug sind Leitwerkmittel (8, 8'; 11, 11') vorgesehen für die dynamische Erzeugung einer Steuerkraft. Diese können auch im (vergrösserten) Rundflügel integriert sein. Die Leitwerkmittel sind ausserhalb des Wirkbereiches des Rotorstrahls seitlich am oder im Gehäuse (2) angeordnet. Im angetriebenen Gleitflug wird der Vortrieb von einem Propeller (5) und der Auftrieb durch das Rundflügelprofil übernommen. |
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| 99 | TURBOCRAFT | EP91908875.0 | 1991-04-03 | EP0505509A1 | 1992-09-30 | VALVERDE, Rene, L. |
| Aéronef possédant un corps sensiblement circulaire présentant un profil longitudinal semblable à celui de l'aile d'un avion, et comportant au moins deux ensembles (15) de pales concentriques à contrarotation disposés à l'intérieur dudit corps afin de créer une veine d'air à portance verticale à travers lesdits ensembles (15), ainsi que des dispositifs générateurs de puissance (6, 13, 21, 23) et des dispositifs (122, 123, 124, 126) destinés à coupler les dispositifs générateurs de puissance aux ensembles de pales (15) afin d'en maintenir le mouvement rotatif. Il comprend également des dispositifs propulseurs (6, 18, 157) couplés aux dispositifs générateurs de puissance afin d'appliquer une poussée horizontale à l'aéronef, des dispositifs de rétro-propulsion (21, 169) comprenant une pluralité de chambres de combustion (104) situées sous les ensembles de pales afin de renforcer ladite veine d'air à portance verticale, ainsi qu'un diffuseur pneumatique (106) disposé sous lesdits ensembles de pales (15) et en communication fluidique avec les chambres de combustion (104) et l'élément d'admission des dispositifs générateurs de puissance afin d'assurer une arrivée d'oxygène destiné à soutenir la combustion dans lesdites chambres de combustion (104) et à soutenir la puissance dans lesdits dispositifs générateurs de puissance (6, 13, 21, 23). Ledit diffuseur comprend des palettes supérieures (7, 101) disposées au-dessus desdits ensembles de pales (15) afin d'admettre de l'air, des palettes inférieures (24) disposées au-dessous dudit diffuseur pneumatique (106) afin d'évacuer l'air, ainsi que des dispositifs respectivement supérieur et inférieur (110) servant à commander lesdites pales. | ||||||
| 100 | Flügelrand-Düsen-VSL-Flugzeug | EP91100127.9 | 1991-01-03 | EP0439014A3 | 1992-01-15 | Teinzer, Harald; Teinzer, Bernd |
Es wird ein Flügelrand-Düsen-Flugzeug vorgeschlagen, welches ein Nur-Flügelflugzeug (1) ist. Mittels einer Radialturbine (5,6) wird ein Gas/Luft-Strom (8,9) erzeugt, der über einen Luftkanal (11) den Randdüsen (4) zugeführt wird. Mit den Randdüsen wird der Gas/Luft-Strom so eingestellt, daß das Flugzeug vertikal starten und Landen, aber auch horizontal fliegen kann. |
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