| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 41 | 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. | ||||||
| 42 | Flugkörper und Verfahren zur Herstellung desselben | EP81109908.4 | 1981-11-26 | EP0080517A1 | 1983-06-08 | Bachmann, Josef |
Der Flugkörper (6) ist ein Ausschnitt aus einem Basiskörper (4), der durch Drehen eines Tragflügelprofils (1) mit seiner Austrittskante um ein Bildungszentrum (B) gebildet wird. Der Durchmesser (d) des Flugkörpers (6) ist 15 - 40 % grösser als der Radius (R) des Basiskörpers (4) und berührt in einem Punkt (7) dessen Umfangslinie (5). Die vom Umfang des Flugkörpers (6) geschnittenen Tragflügelprofile (1) bilden Profilfragmente, deren Unterseite gegen die Profiloberseite gewölbt wird. Es entsteht auf diese Weise ein gegenüber anderen Flugkörpern eigenstabiler Flugkörper, dessen grosse Fläche sich besonders für das Fliegen mit Energie aus Solarzellen eignet. |
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| 43 | MODULAR FUSELAGE SECTIONS FOR VERTICAL TAKE OFF AND LANDING DISTRIBUTED AIRFRAME AIRCRAFT | US15593607 | 2017-05-12 | US20180244364A1 | 2018-08-30 | Carlos Alexander Fenny; Rohn Lee Olson; Andrew James Zahasky |
| An aircraft capable of vertical takeoff and landing and stationary flight includes a distributed airframe coupled to a modular fuselage. The modular fuselage has a longitudinal axis substantially parallel to a rotational axis of three or more propellers. The modular fuselage includes a rear module substantially disposed within a perimeter of the distributed airframe, a front module removably connected to the rear module and substantially aligned with the longitudinal axis. One or more engines or motors are disposed within or attached to the distributed airframe or fuselage. The three or more propellers are proximate to a leading edge of the distributed airframe, distributed along the distributed airframe, and operably connected to the one or more engines or motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight. | ||||||
| 44 | SYSTEM AND METHOD FOR FLYING TRUCKS | US15144708 | 2016-05-02 | US20160318609A1 | 2016-11-03 | Peter Sturt Lynn; Becker van Niekerk; Saul Thomas Griffith |
| A tethered wing comprising an aerodynamic wing body defining external and internal faces and a plurality of rotors disposed on the wing body. The tether wing can further include a tether configured to extend and retract. The tethered wing can be configured to perform a payload pickup maneuver that includes coupling the tether to a payload with the tether in an extended configuration, taking off in a vertical flight configuration proximate to the tethered payload, transitioning to a horizontal flight configuration over the tethered payload and circling and ascending over the tethered payload to lift the tethered payload into the air via the tether. | ||||||
| 45 | VERTICAL TAKE-OFF AND LANDING (VTOL) AERIAL VEHICLE AND METHOD OF OPERATING SUCH A VTOL AERIAL VEHICLE | US14088662 | 2013-11-25 | US20140151494A1 | 2014-06-05 | Tomislav Cvrlje |
| A Vertical Take-off and Landing (VTOL) aerial vehicle (1, 46), e.g. a rotorcraft with long range and high cruising speed capability. The aerial vehicle (1, 46) has a torus-type fuselage (2) with radial inside a duct (5) and at least one main rotor (13, 26). A pair of lateral wings (40) are attached opposed to each other outside the fuselage (2) and at least one engine (18) drives said at least one main rotor (13, 26) and at least two propulsion means (24) fitted to each of said wings (40). The invention relates as well to a method of operating such a VTOL aerial vehicle (1, 46). | ||||||
| 46 | Lift Propulsion and Stabilizing System and Procedure For Vertical Take-Off and Landing Aircraft | US13822665 | 2011-04-12 | US20130251525A1 | 2013-09-26 | Manuel M. Saiz |
| Lift propulsion and stabilizing system and procedure for vertical takeoff and landing aircraft that consists in applying simultaneously and combined as lifters during the initial portion of the climb and at the end of the descent of: a) some fans or electric turbines, EDF, and b) at least one rotor with external blades and/or rotary and/or c) the engine flow directed downwards and/or d) pressure air jets injected on leading edges control fins, and/or e) water jets and/or f) supplemented with aerodynamic lift produced during frontal advance of the aircraft, the stabilization is achieved by the gyroscopic stiffness of the rotor and two or more lifting fans oscillating fins and/or air jets located on two or stabilizers more peripheral points in a plane perpendicular to the vertical axis of the aircraft. | ||||||
| 47 | AERODYNAMIC VEHICLE HAVING A VARIABLE GEOMETRY, CO-PLANAR, JOINED WING | US10801750 | 2004-03-16 | US20070120007A1 | 2007-05-31 | Rudolph Yurkovich |
| An aerodynamic vehicle is comprised of a pair of forward wing sections and a pair of rearward wing sections that are connected together by four pivot assemblies as a four-bar linkage. The four-bar linkage surrounds an opening provided between the forward wing sections and rearward wing sections. Movement of the wing sections varies the cumulative area of the wing sections, and adjusts the shape of the opening between the forward wing sections and rearward wing sections. Movement of the wing sections improves the aerodynamic performance of the vehicle and allows the wing sections to assume optimum configurations for operation of the vehicle at high speed and low speed. | ||||||
| 48 | Damage Resistant Aircraft | US11561392 | 2006-11-18 | US20070114326A1 | 2007-05-24 | Francis Gentile |
| Integration of structure and aerodynamic shape results in a Damage Resistant Unmanned Aircraft, Capable of surviving ground handling and impacts with plants, wires, solid objects and water. The structure dismantles for transport and storage into a small space, that is resistant to damage. The aerodynamic arrangement has a improved ability to fly controllably in the gusty environment that causes difficulty for small light weight aircraft. A method of mounting pneumatic and fabric shapes onto a Damage Resistant Aircraft with parts facilitating a round structure. Use of the pneumatic shapes to adjust the length and stiffness of the post. The post produces tension on the structure that It presses against. Inflatable post ends and an attachment system. Multi piece removable wing tips which allow deflation, access and small folding volume of the inflatable structure. All tension rudders are formed inside the net structure where it is protected from damage. | ||||||
| 49 | Aircraft of compact dimensions | US11353053 | 2006-02-14 | US20070018037A1 | 2007-01-25 | Pietro Perlo; Denis Bollea |
| The aircraft comprises a fuselage, a main wing substantially of disc-like shape positioned above the fuselage, and a secondary wing which intersects the fuselage and is provided with movable control parts. The aircraft further comprises a main propulsion system including an internal combustion engine intended to drive a propeller positioned at the rear of the fuselage and a secondary propulsion system for the propulsion of the aircraft in a direction perpendicular to the ground. The secondary propulsion system includes a matrix of nozzles positioned on the lower surface of the secondary wing and arranged to emit the exhaust gases coming from the main engine in the form of micro-jets. The main propeller propulsion system and the secondary nozzle propulsion system are selectively controllable in such a way that the aircraft is able to perform three different take-off modes, that is to say a first, conventional take-off mode in which only the main propulsion system is used, a second (STOL) take-off mode in which both the main propulsion system and the secondary propulsion system are used, and a third (VTOL) take-off mode in which only the secondary propulsion system is used. | ||||||
| 50 | Ring-shaped wing helicopter | US10295796 | 2002-11-15 | US20030122033A1 | 2003-07-03 | Hengwei Gao |
| The invention discloses a new type ring-shaped wing helicopter, which is similar to a flying saucer in appearance with lift and attitude control torque brought by the blades of two ring-shaped wings rotating in opposite directions between the inlet cascade and the outlet cascade of the circular fringe of wing fuselage. The helicopter of this kind without any outer rotors has high flying speed, good hydrodynamic form and simple-small structure and extensive securitiesnullthe crewman can easy escape quickly by ejecting upwardly in danger, the body of the helicopter allows slight impact with other objects during routine flight, and the running parts with high kinetic energy cannot threaten the personnel inside and outside the helicopter directly in its taking off and landing processes. | ||||||
| 51 | Vertical take off and landing aircraft | US157730 | 1998-09-21 | US6050520A | 2000-04-18 | Stanley J. Kirla |
| An aircraft for vertical take off and landing is comprised of a rotor assembly mounted on a rotating drive shaft extending from the top of a cabin. The rotor assembly is comprised of a truncated-cone top, a spaced apart circular bottom, and internal vanes running radially, between the top and bottom, forming an air impeller. In operation, air is drawn through the central air intake of the top and discharged through an annular nozzle around the circumference of the rotor assembly. As the top rotates, additional air is rammed through scoops mounted at an angle to radii of the top, on the surface of the top. The torque applied to the cabin, due to rotation by the engine of the rotor assembly, is countered by the reaction force generated by a plurality of tabs extending from the cabin sidewall into the airstream flowing downwardly from the nozzle. | ||||||
| 52 | Body lift airplane assembly | US971301 | 1997-11-17 | US5971321A | 1999-10-26 | Ronald L. Libengood |
| A body lift airplane assembly including 1) a main air lift body assembly of substantial length and width; 2) a landing gear/wheel assembly retractably connected to the main air lift body assembly; 3) a fixed wing assembly secured to and extended above the main air lift body assembly and having a fixed wing member of a length equal to the width of the main air lift body assembly; 4) an engine propulsion power assembly having a pair of spaced jet engine pod assemblies mounted within engine cut-out portions in outer edges of the main air lift body assembly; and 5) a fin and rudder assembly of a V-shape connected to a central rear portion of the main air lift body assembly. The main air lift body assembly includes a main body assembly having outer peripheral side and rear edges formed with downwardly extended arcuate air lift portions to provide air lift characteristics to the overall main air lift body assembly. The main air lift body assembly is provided with a passenger compartment section and a pilot control section and access thereto through an access escalator assembly and not dependent on external airport facility structures for loading and unloading. The jet engine pod assemblies each are operable to receive air flow from both above and below the main body assembly of the main air lift body assembly to increase the fuel combustion efficiency. | ||||||
| 53 | Aerolift mechanism | US998702 | 1997-12-29 | US5829714A | 1998-11-03 | William Francis Lechtenberg |
| A free movement, lift mechanism employing a spinning disc utilizing Bernoulli's Theorem and the derivative Coanda and Couette effects augmented by centrifugal force. Lift control is provided by variation in rotational velocity of the disc, by variation in the width of a Couette space and by variation in the amount of air entering the Couette space. Strategically placed vanes provide stabilizing control. | ||||||
| 54 | Control system for jet propelled vehicle | US267324 | 1988-11-04 | US4901948A | 1990-02-20 | Peter M. Panos |
| A vehicle capable of omnidirectional movement employing a jet engine and a plurality of directional jet nozzles communicating with said engine, and a single controller means united with said nozzles to cause omnidirectional movement of said vehicle and control the acceleration and deceleration of said vehicle. | ||||||
| 55 | Amphibious discoidal aircraft | US646791 | 1984-09-04 | US4674708A | 1987-06-23 | Gilbert del Castillo |
| An aircraft comprising a discoidal fuselage having a planar upper surface and containing at least one vertical duct extending longitudinally therethrough, an impeller located within the duct for producing an upward flow of gas, and a gas flow director movably mounted with respect to said duct. The vertical duct is central to the fuselage. The impeller is a vertical turbojet engine. The gas director comprises a central conical member, an upper annular flow control member, and a plurality of radially spaced apart vent controls. The vent controls are hydraulic cylinders. A hatch is mounted about the bottom opening of said duct. The hatch is movable such that one position seals the duct from the entry of liquids. An air passageway extends into and communicates with the duct. | ||||||
| 56 | Aircraft with circular wing | US951198 | 1978-10-13 | US4312483A | 1982-01-26 | Nicolae Bostan |
| An aircraft is provided with a circular wing member which is rotatably mounted to a fuselage member. The circular wing member provides lift for horizontal flight and also provides gyroscopic stabilization of aircraft attitude. The circular wing member is substantially free of aerodynamically active flight control or propulsion members and, in a preferred embodiment, has a concentration of mass at its outer rim. The fuselage is provided with propulsion means for effecting and controlling vertical and horizontal flight. The propulsion means provides horizontal or vertical thrust along vectors which pass through the aircraft center of mass. | ||||||
| 57 | Annular wing | US43911 | 1979-05-30 | US4307856A | 1981-12-29 | Harold J. Walker |
| An annular wing particularly suited for use in supporting in flight an aircraft characterized by the absence of directional stabilizing surfaces. The wing comprises a rigid annular body of a substantially uniformly symmetrical configuration characterized by an annular positive lifting surface and cord line coincident with the segment of a line radiating along the surface of an inverted truncated cone whereby a decalage is established for the leading and trailing semi-circular portions of the body, relative to instantaneous line of flight, and a dihedral for the laterally opposed semi-circular portions of the body, relative to the line of flight, the direction of flight and climb angle or glide slope angle being established by selectively positioning the center of gravity of the wing ahead of the aerodynamic center along the radius coincident with an axis for a selected line of flight. | ||||||
| 58 | Flying disc | US15410 | 1979-02-26 | US4214720A | 1980-07-29 | Edwin R. DeSautel |
| A flying disc capable of vertical takeoff, hovering, or powered horizontal flight. The disc includes a discoidal wing that is circular and includes a convex surface on an upper side and a concave lower surface. The wing also includes an inward leading edge that defines a circular opening centered on an upright central axis. The arcuate surfaces converge at the leading edge and at an outer concentric trailing edge. The discoidal wing is freely rotatable on a central support structure that also supports a cockpit. Two sets of turbine blades are affixed to the discoidal wing adjacent the leading edge. Thrust producing engines are mounted to the central support structure to direct thrust radially outward through the turbine blades. This results in rotation of the discoidal wing and produces lift. The angle of thrust may be adjusted such that the thrust is directed only across one or the other set of turbine blades or any selected variation between extreme positions to change the lift characteristics. A set of compressor blades is provided about an upper surface of the disc adjacent the cockpit. The compressor blades rotate with the discoidal wing to receive and direct air downwardly into the central support structure. They supply combustion air for the engine and reduce the air pressure above the disc. Horizontal thrust engines are supplied below the concave wing surface to provide horizontal thrust. Steering and rotational stabilization of the cockpit and central support structure is provided by a thrust diverting mechanism. | ||||||
| 59 | Aircraft with circular wings | US639103 | 1975-12-09 | US4044972A | 1977-08-30 | Leif Anker-Holth |
| An aircraft has two concentric wings of substantially equal diameters, the wings being connected to each other and stayed by an elongated central corridor which is located beneath a central engine duct disposed in the plane of the upper wing. | ||||||
| 60 | Aircraft | US3689011D | 1969-07-11 | US3689011A | 1972-09-05 | TORELLI DORANT |
| A heavier than air aircraft having an elongated oval shaped single wing of a substantial thickness at its center to enclose a hub portion concentric with the vertical axis of the aircraft, the wing tapering toward its periphery from the thickness at the hub. The aircraft has a power driven rotor having driving blades to propel the aircraft in a vertical direction and jet engines mounted in the wing for propelling the aircraft along its horizontal course. The surfaces of the wing are so contoured as to assist the aerodynamic forces in stabilizing and guiding the aircraft while under power or in a gliding state.
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