| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 141 | Modular and morphable air vehicle | US15205162 | 2016-07-08 | US09610817B1 | 2017-04-04 | 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 manned. The air module may have two rotors, which may be ducted fans. The air module may include a parachute, an airbag and landing gear. | ||||||
| 142 | A FLIGHT CONTROL DEVICE FOR AN AIRCRAFT | US15120413 | 2015-02-04 | US20170008614A1 | 2017-01-12 | Bruno TILLY; Nicolas RAVOUX |
| The invention relates to a flight control device for an aircraft, the device comprising a mount, a lever pivotally mounted on the mount, and mechanical means for generating a return force for the lever, said means including a spring and a first motor member that are arranged so that a first end of the spring is constrained to move in rotation with the lever and a second end of the spring is constrained to move in rotation with an outlet shaft of the first motor member. According to the invention, the flight control device includes an electrical assistance system for assisting said mechanical means for generating a return force. | ||||||
| 143 | Aircraft With A Plurality Of Engines Driving A Common Driveshaft | US15204547 | 2016-07-07 | US20160311530A1 | 2016-10-27 | Frick A. Smith |
| An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft. | ||||||
| 144 | Providing Services Using Unmanned Aerial Vehicles | US15147762 | 2016-05-05 | US20160244163A1 | 2016-08-25 | Eric Peeters; Eric Teller; William Graham Patrick |
| Embodiments described herein may help to provide support via a fleet of unmanned aerial vehicles (UAVs). An illustrative medical-support system may include multiple UAVs, which are configured to provide support for a number of different situations. Further, the medical-support system may be configured to: (a) identify a remote situation, (b) determine a target location corresponding to the 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 situation, and (d) cause the selected UAV to travel to the target location to provide support. | ||||||
| 145 | Power safety instrument system | US14715236 | 2015-05-18 | US09352849B2 | 2016-05-31 | James M. McCollough; Erik Oltheten; Nicholas Lappos |
| A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available. | ||||||
| 146 | UNIVERSAL MULTI-ROLE AIRCRAFT PROTOCOL | US14843565 | 2015-09-02 | US20160107657A1 | 2016-04-21 | Sydney Robert CURTIS |
| The Curtis Protocol, an aircraft control interface, is provided. The Curtis Protocol standardizes the division and selection of aircraft flight regimes and flight modes within the selected flight regime. | ||||||
| 147 | Vertical take-off and landing aircraft with tiltrotor power for use on land and in air | US14128992 | 2012-06-06 | US09254916B2 | 2016-02-09 | Zhaoxi Yang |
| A vertical take-off and landing aircraft with tiltable power for use on land and in the air includes: a body (3) provided with a drive device; wheels (8) being controlled to make the body move on the ground; and a front thruster (1) and a rear thruster (2) controlling the body to fly or take off/land, wherein transmission brace rods (5) are arranged on both sides of the body, and a first pivot (9) passes transversely through the body and is connected to the transmission brace rods on both sides of the body; wherein the front thruster is fixed on front ends of the transmission brace rods, and the rear thruster is fixed on rear ends of the transmission brace rods; wherein the central axes of the front and rear thrusters are perpendicular to the plane formed by the two transmission brace rods. By controlling a tilting angle of the front/rear thrusters, this aircraft has two basic functions of vertical take-off/landing and horizontal flight, so as to facilitate conversion between land travel and air flight. During flight in the air, the aircraft body always remains in horizontal state, thereby making the occupants feel comfortable and providing them with broad vision so as to operate the aircraft safely. | ||||||
| 148 | Providing Services Using Unmanned Aerial Vehicles | US14705879 | 2015-05-06 | US20150353195A1 | 2015-12-10 | Eric Peeters; Eric Teller; William Graham Patrick |
| Embodiments described herein may help to provide support via a fleet of unmanned aerial vehicles (UAVs). An illustrative medical-support system may include multiple UAVs, which are configured to provide support for a number of different situations. Further, the medical-support system may be configured to: (a) identify a remote situation, (b) determine a target location corresponding to the 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 situation, and (d) cause the selected UAV to travel to the target location to provide support. | ||||||
| 149 | SYSTEM, APPARATUS AND METHOD FOR LONG ENDURANCE VERTICAL TAKEOFF AND LANDING VEHICLE | US14507198 | 2014-10-06 | US20150336666A1 | 2015-11-26 | 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. | ||||||
| 150 | Universal multi-role aircraft protocol | US14516464 | 2014-10-16 | US09126677B1 | 2015-09-08 | Sydney Robert Curtis |
| The Curtis Protocol, an aircraft control interface, is provided. The Curtis Protocol standardizes the division and selection of aircraft flight regimes and flight modes within the selected flight regime. | ||||||
| 151 | Sustained over-the-horizon vertical takeoff and landing sensing system | US13866489 | 2013-04-19 | US08948928B2 | 2015-02-03 | Mark R. Alber; Timothy Fred Lauder; Jonathan Hartman; Bryan Clark Holasek |
| An electrically powered of the vertical takeoff and landing aircraft configured for use with a tether station having a continuous power source is provided including at least one rotor system. The vertical takeoff and landing aircraft additionally has an autonomous flight control system coupled to the continuous power source. The autonomous flight control system is configured to operate an electrical motor coupled to the at least one rotor system such that the vertical takeoff and landing aircraft continuously hovers above the tether station in a relative position. The vertical takeoff and landing aircraft also includes a detection system for detecting objects at a distance from the vertical takeoff and landing aircraft. | ||||||
| 152 | WING ADJUSTING MECHANISM | US14378633 | 2013-02-13 | US20150028155A1 | 2015-01-29 | Johannes Reiter |
| The present invention relates to a device for generating aerodynamic lift and in particular an aircraft (100) for vertical take-off and landing. A wing arrangement (110) comprises at least one propulsion unit (111), wherein the propulsion unit (111) comprises a rotating mass which is rotatable around a rotary axis (117). The wing arrangement (110) is mounted to a fuselage (101) such that the wing arrangement (110) is tiltable around a longitudinal wing axis (112) of the wing arrangement (110) and such that the wing arrangement (110) is rotatable with respect to the fuselage (101) around a further rotary axis that differs to the longitudinal wing axis (112). An adjusting mechanism adjusts a tilting angle of the wing arrangement (110) around the longitudinal wing axis (112) under influence of a precession force (Fp) which forces the wing arrangement (110) to tilt around the longitudinal wing axis (112). | ||||||
| 153 | SYSTEM, A METHOD AND A COMPUTER PROGRAM PRODUCT FOR MANEUVERING OF AN AIR VEHICLE WITH TILTABLE PROPULSION UNIT | US14372060 | 2013-01-10 | US20140339372A1 | 2014-11-20 | Guy Dekel; Lior Zivan; Yoav Efraty; Amit Wolff; Avner Volvoick |
| A control system configured to control a deceleration process of an air vehicle which comprises at least one tiltable propulsion unit, each of the at least one tiltable propulsion units is tiltable to provide a thrust whose direction is variable at least between a general vertical thrust vector direction and a general longitudinal thrust vector direction with respect to the air vehicle. | ||||||
| 154 | VERTICAL TAKEOFF AND LANDING (VTOL) SMALL UNMANNED AERIAL SYSTEM FOR MONITORING OIL AND GAS PIPELINES | US13772161 | 2013-02-20 | US20140236390A1 | 2014-08-21 | Farrokh Mohamadi |
| Extended-range monitoring and surveillance of facilities and infrastructure—such as oil, water, and gas pipelines and power lines—employs autonomous vertical take-off and landing (VTOL) capable, small unmanned aerial system (sUAS) aircraft and docking platforms for accommodating the sUAS aircraft. Monitoring and surveillance of facilities using one or more embodiments may be performed continually by the sUAS flying autonomously along a pre-programmed flight path. The sUAS aircraft may have an integrated gas collector and analyzer unit, and capability for downloading collected data and analyzer information from the sUAS aircraft to the docking platforms. The gas collector and analyzer unit may provide remote sensing and in-situ investigation of leaks and other environmental concerns as part of a “standoff” (e.g., remote from operators of the system or the facilities) survey that can keep field operators out of harm's way and monitor health of the environment. | ||||||
| 155 | Aircraft with freewheeling engine | US13442544 | 2012-04-09 | US08720814B2 | 2014-05-13 | Frick A. Smith |
| An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft. | ||||||
| 156 | ELECTRICALLY POWERED AERIAL VEHICLES AND FLIGHT CONTROL METHODS | US14046729 | 2013-10-04 | US20140097290A1 | 2014-04-10 | Markus Leng |
| An aerial vehicle includes at least one wing, a plurality of thrust producing elements on the at least one wing, a plurality of electric motors equal to the number of thrust producing elements for individually driving each of the thrust producing elements, at least one battery for providing power to the motors, and a flight control system to control the operation of the vehicle. The aerial vehicle may include a fuselage configuration to facilitate takeoffs and landings in horizontal, vertical and transient orientations, redundant control and thrust elements to improve reliability and means of controlling the orientation stability of the vehicle in low power and multiple loss of propulsion system situations. Method of flying an aerial vehicle includes the variation of the rotational speed of the thrust producing elements to achieve active vehicle control. | ||||||
| 157 | Personal Aircraft | US13764697 | 2013-02-11 | US20130214086A1 | 2013-08-22 | 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. | ||||||
| 158 | SYSTEM, APPARATUS AND METHOD FOR LONG ENDURANCE VERTICAL TAKEOFF AND LANDING VEHICLE | US13397569 | 2012-02-15 | US20130206921A1 | 2013-08-15 | James Donald Paduano; Paul Nils Dahlstrand; John Brooke Wissler |
| 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. | ||||||
| 159 | Power Safety Instrument System | US13641325 | 2010-12-22 | US20130120165A1 | 2013-05-16 | James M. McCollough; Erik Oltheten; Nicholas Lappos |
| A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available. | ||||||
| 160 | Unmanned Aerial Vehicle and Method of Operation | US13656587 | 2012-10-19 | US20130099048A1 | 2013-04-25 | CHRISTOPHER E. FISHER; JOHN P. ZWAAN; MARC L. SCHMALZEL; STEVEN CHAMBERS; JUSTIN B. McALLISTER |
| A method of unmanned aerial vehicle(UAV) flight includes providing horizontal thrust in-line with the direction of forward flight of the UAV(110)using at least one electric motor(120), providing primary vertical lift for the UAV(110) during the forward flight using a fixed and non-rotating wing(125), repositioning the at least one electric motor(120′)to provide vertical thrust during transition of the UAV(110)to vertical flight(A) for descent(E),landing the UAV(110)on a surface(270) using a vertical approach after the motor repositioning, and deploying an anchor(150) to secure the UAV(110)to a surface(270). | ||||||
QQ群二维码
意见反馈
意见反馈