| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 241 | Modular and Morphable Air Vehicle | US14684995 | 2015-04-13 | US20150217613A1 | 2015-08-06 | John W. Piasecki; Frederick W. Piasecki; Brian Geiger; Douglas Johnson; David Pitcairn |
| 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. | ||||||
| 242 | Providing emergency medical services using unmanned aerial vehicles | US13730298 | 2012-12-28 | US09051043B1 | 2015-06-09 | Eric Peeters; Eric Teller; William Graham Patrick |
| Embodiments described herein may help to provide medical support via a fleet of unmanned aerial vehicles (UAVs). An illustrative medical-support system may include multiple UAVs, which are configured to provide medical support for a number of different medical situations. Further, the medical-support system may be configured to: (a) identify a remote medical situation, (b) determine a target location corresponding to the medical situation, (c) select a UAV from the fleet of UAVs, where the selection of the UAV is based on a determination that the selected UAV is configured for the identified medical situation, and (d) cause the selected UAV to travel to the target location to provide medical support. | ||||||
| 243 | Modular and morphable air vehicle | US13068601 | 2011-05-16 | US09045226B2 | 2015-06-02 | John W. Piasecki; Frederick W. Piasecki; Brian Geiger; Douglas Johnson; David Pitcairn |
| 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. | ||||||
| 244 | Sky condenser with vertical tube compression and pressurized water utilization | US13998564 | 2013-11-12 | US20150128597A1 | 2015-05-14 | Daniel Keith Schlak |
| A floated condenser extracts water from the sky. The condenser is part of or supplemental to a typical buoyed wind turbine set, comprising lift element, wind turbine, retention cable, electrical output, and base. The cable is hollow or coextensive with a lumen, the inner diameter thereof is water impermeable. The hollow/lumen stacks water over an accumulator, effecting a static base pressure p=ρgh. This pressure makes the water utilizable. After pressure multiplication—via a hydrostatic piston—or not, a first stream of water electrolyzes into liquid hydrogen and oxygen, one or both stored/sold directly. Another stream of water drives a turbine/motor or series hydroelectric turbines/motors, powering electrolysis and/or grid, the water then stored at moderate pressure for water utilities. Excess power from the wind turbine also supplements electrical output. A conductor runs along the cable. Gasified hydrogen is routed via the cable, lifting the condenser/turbine/kite. | ||||||
| 245 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT | US14384053 | 2013-03-12 | US20150053826A1 | 2015-02-26 | Masayoshi Tsunekawa; Tetsuya Tamura |
| There is provided a vertical take-off and landing aircraft including: a propulsion mechanism for generating lift and thrust; a power supply unit (e.g. an engine as a power source) for supplying power to the propulsion mechanism; a main frame for supporting the engine, a seat, and a landing undercarriage; a sub-frame for supporting the propulsion mechanism; a frame coupling unit for rotatably coupling the main frame and the sub-frame; and a control stick connected to the sub-frame, so that an occupant sitting on a seat operates a control stick thereby to move the sub-frame relative to the main frame so as to change the orientation of the propulsion mechanism. | ||||||
| 246 | SYSTEM, APPARATUS AND METHOD FOR LONG ENDURANCE VERTICAL TAKEOFF AND LANDING VEHICLE | US14507228 | 2014-10-06 | US20150021430A1 | 2015-01-22 | JAMES DONALD PADUANO; PAUL NILS DAHLSTRAND; JOHN BROOKE WISSLER; ADAM WOODWORTH |
| A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends. | ||||||
| 247 | Vertical Takeoff and Landing (VTOL) Air Vehicle | US14270320 | 2014-05-05 | US20150014475A1 | 2015-01-15 | Dana J. Taylor; Phillip T. Tokumaro; Bart Dean Hibbs; William Martin Parks; David Wayne Ganzer; Christopher Eugene Fisher; Jason Sidharthadev Mukherjee; Joseph Frederick King |
| A flight control apparatus for fixed-wing aircraft includes a first port wing and first starboard wing, a first port swash plate coupled between a first port rotor and first port electric motor, the first port electric motor coupled to the first port wing, and a first starboard swash plate coupled between a first starboard rotor and first starboard electric motor, the first starboard electric motor coupled to the first starboard wing. | ||||||
| 248 | Electric powered rotary-wing aircraft | US12018217 | 2008-01-23 | US08931732B2 | 2015-01-13 | Jayant Sirohi; Timothy Fred Lauder; Mark R. Alber; Daniel Bazzani |
| A rotary-wing aircraft with an electric motor mounted along an axis of rotation to drive a rotor system about the axis of rotation. | ||||||
| 249 | METHOD AND MEANS TO CONTROL THE POSITION AND ATTITUDE OF AN AIRBORNE VEHICLE AT VERY LOW VELOCITY | US13682979 | 2012-11-21 | US20140138476A1 | 2014-05-22 | Per Olof Bystrom |
| A vehicle equipped with two or more propulsion units, each, for example, consisting of engine with propeller, with their thrust principally directed vertically along a z-axis, such vehicle characterized by that each propulsion unit can be controlled by rotation around two axes mainly perpendicular to the z-axis and that the propulsion units are positioned some distance apart in the z-direction enabling such control of the attitude of the propulsion units to obtain: a) lateral force without attendant moment around the center-of-gravity of the vehicle to control the lateral position of the vehicle, or b) a moment around the center-of-gravity of the vehicle without attendant lateral force to control the lateral attitude of the vehicle, or c) combination of (a) and (b) thereby to simplify the implementation of a system to control the position and attitude of the vehicle whether such control system is manipulated manually, automatically or in a combination thereof. | ||||||
| 250 | Personal aircraft | US13229717 | 2011-09-10 | US08393564B2 | 2013-03-12 | Ilan Kroo |
| A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight. | ||||||
| 251 | Modular and morphable air vehicle | US13068601 | 2011-05-16 | US20110315806A1 | 2011-12-29 | John W. Piasecki; Frederick W. Piasecki; Brian Geiger; Douglas Johnson; David Pitcairn |
| 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. | ||||||
| 252 | SPACECRAFT PROPULSION SYSTEM WITH GYROSCOPIC MECHANISM | US12452971 | 2008-09-28 | US20100176248A1 | 2010-07-15 | Mehmet Terziakin |
| A propulsion method employing gyroscopes (1,2) with electric motors (4) 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. | ||||||
| 253 | ELECTRIC POWERED ROTARY-WING AIRCRAFT | US12018217 | 2008-01-23 | US20090140095A1 | 2009-06-04 | Jayant Sirohi; Timothy Fred Lauder; Mark R. Alber; Daniel Bazzani |
| A rotary-wing aircraft with an electric motor mounted along an axis of rotation to drive a rotor system about the axis of rotation. | ||||||
| 254 | Aircraft | US10934634 | 2004-09-03 | US07364114B2 | 2008-04-29 | Aloys Wobben |
| The present invention concerns an aircraft having a plurality of lifting and thrust rotors, with an electric motor and an inverter for each motor. In order to provide an aircraft having a greater payload, connecting bars are provided between the motors. In that respect the invention is based on the realization that, if such connecting bars are arranged in the manner of a latticework, they can provide a light but nonetheless stable structure for the aircraft, and that structure can carry correspondingly greater loads. | ||||||
| 255 | AIRCRAFT | US11859657 | 2007-09-21 | US20080006737A1 | 2008-01-10 | Aloys Wobben |
| The present invention concerns an aircraft having a plurality of lifting and thrust rotors, with an electric motor and an inverter for each motor. In order to provide an aircraft having a greater payload, connecting bars are provided between the motors. In that respect the invention is based on the realization that, if such connecting bars are arranged in the manner of a latticework, they can provide a light but nonetheless stable structure for the aircraft, and that structure can carry correspondingly greater loads. | ||||||
| 256 | 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. | ||||||
| 257 | Multi-service common airframe-based aircraft | US756154 | 1996-11-26 | US5897078A | 1999-04-27 | Robert W. Burnham; Michael F. Fitzpatrick; Dennis A. Muilenberg; Joseph K. Schoebelen; Laurence B. Trollen |
| A modular approach to the manufacture of high performance military aircraft allows different aircraft to be manufactured at affordable cost and with high part number commonality. An aircraft so constructed includes a delta wing; a forebody section, including a cockpit, which is mounted to the front of the wing; and a propulsion system support frame mounted beneath the forebody section and the underside of the wing. The propulsion system is supported within this frame. The aircraft can also include an aftbody section mounted to the aft end of the wing, which includes a 2-D variable thrust vectoring nozzle and a pair of canted vertical tails. The forebody section includes a chin inlet below the cockpit. The wing is preferably constructed using thermoplastic welding. | ||||||
| 258 | 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. | ||||||
| 259 | Split rotor shaft driven lift fan | US772672 | 1996-12-20 | US5820345A | 1998-10-13 | Rollin G. Giffin, III; Lawrence W. Dunbar; Ronald F. Petsch |
| A split fan for providing lift for an aircraft is described. In one embodiment, a main engine shaft extends to the split fan, and a portion of the split fan is located at an elevation above the main engine shaft and a portion of the split fan is located at an elevation below the main engine shaft. In the one embodiment, the split fan includes an outer casing configured to be mounted to a fuselage of the aircraft, a first stage rotor including a shaft, a gear secured to the shaft, and a plurality of rotor blades radially extending from the shaft. The split fan also includes a second stage rotor including a shaft, a gear secured to the shaft, and a plurality of blades radially extending from the shaft. A drive shaft having a first end and a second end is coupled at the drive shaft first end to the main engine shaft. A drive gear is located at the second end of the drive shaft, and the first stage rotor gear and the second stage rotor gear are coupled to the drive gear so that as the drive gear rotates, the first stage rotor gear rotates in a first direction and the second stage rotor gear rotates in a second direction. | ||||||
| 260 | Aircraft with a plurality of propellers, a pipe structure for thereon holdable wings, for vertical take off and landing | US330668 | 1989-03-30 | US4982914A | 1991-01-08 | Karl Eickmann |
| An aircraft has a pair of wing portions with propellers of a propeller pair which are driven and synchronized by a fluid transmission between the power plant and the propellers. A fluid line structure keeps most components of the craft together and consists preferredly of three pipes which are also utilized to carry the driving fluid to and from the motors, to hold the motors and to hold the wings. The take over of a plurality of functions by the interior pipe structure reduces weight and secures safe and economic operation of the craft. The pipe structure can be pivoted in respective bearings to effect the pivotal movement of the propellers and wing portions for either vertical take off and landing or for horizontal flight. The pipe structure is built by pipes without bends in order to make the cleaning of the interiors of the pipes from dirt and from remainders of welding possible. Ribs and holding portions are provided on the structure for assembly and/or disassembly of the wing portions of the pipe structure. | ||||||
QQ群二维码
意见反馈
意见反馈