| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 101 | 飞行器 | CN201620447947.1 | 2016-05-17 | CN205916327U | 2017-02-01 | 胡华智; 潘旭; 靳洪胜 |
| 本实用新型公开了一种飞行器，包括飞行器主体、设置于所述飞行器主体上的机臂组件、及设置于所述机臂组件上的动力装置，所述动力装置包括驱动件、及与所述驱动件连接的螺旋桨，所述螺旋桨的旋转面沿所述机头的行进方向偏转、并与所述飞行器主体倾斜布置。当飞行器前行时，飞行器主体与水平面平行，通过将飞行器主体上表面设计为弧面，下表面设计为平面，使气流经过飞行器主体时在上、下表面产生压力差从而产生爬升力，由此为所述飞行器主体起到托举作用，由此来降低对所述螺旋桨的依赖，降低所述螺旋桨的负载，从而大大降低电机功耗以达到在同样的电池和动力系统配置下飞行器能够具备更长的续航时间。 | ||||||
| 102 | 双层旋翼直升飞机倾斜控制器 | CN200920125353.9 | 2009-04-17 | CN201376668Y | 2010-01-06 | 彭凯; 李林; 陈古力; 彭纪钢 |
| 本实用新型公开的双层旋翼直升飞机倾斜控制器，由机身上管状主轴，主轴上的上下旋翼座，安装旋翼，三套滚轮连接传动件，滚轮支架等组件连接组合而成，飞行员通过控制杆转盘对倾斜面控制杆的操作，能使上下旋翼在平面内可向任一方向同时倾斜，支撑着上下旋翼面保持平衡，下旋翼作正方向旋转，同时内圆锥形齿轮带动滚轮转动，滚轮带动上旋翼圆锥形齿轮转动。通过内外圆锥形齿轮与滚轮的连结方式，使上旋翼反方向转动。使上下旋翼旋转方向相反，滚轮支架与上下旋翼座都安装在球形座上，就能使上下旋翼在平面内同时向任一方向倾斜。经过操纵控制部分的试验，比较现有的直升飞机控制系统，有操作灵活，飞行安全，结构简单的特点，设备维修、保养方便。 | ||||||
| 103 | MULTIPURPOSE AIR VEHICLE | US15575806 | 2016-09-26 | US20180346113A1 | 2018-12-06 | TAE-JUNG CHANG |
| Disclosed is a multipurpose air vehicle including a frame (1) on which a propeller (11) and a mechanical unit (10) equipped with an engine are mounted, and a cabin (2) is coupled inside the frame (1). The frame (1) is constructed by upper and lower circular plates (101, 102) and curved posts (111, 112, 113, 114) that interconnect the upper and lower circular plates (101, 102), and is provided with two or more arms (12) that can protrude and retract, and a propeller (11) is provided on the tip end of each arm (12). The cabin (2) includes a circular plate member (3) and further includes at least four connectors (21) provided on the front, the rear, the left, and the right ends thereof, and each connector (21) has a tip end installed on a rail (13) of the frame (1) so as to guide pivoting of the cabin (2). The multipurpose air vehicle may freely perform upward and downward movement and forward and rearward movement, and thus may be used anywhere in the air, ground, or water. Moreover, the multipurpose air vehicle may allow the cabin (2) to maintain horizontal balance and to provide a lift force as needed, regardless of the flying angle during the upward or downward movement of the air vehicle. | ||||||
| 104 | Flying Object | US15770254 | 2016-10-28 | US20180312246A1 | 2018-11-01 | Yang Woo NAM |
| A flying object according to the present invention has been developed to have a plurality of rotor blades or jet engines, and to reduce the risk of a crash even if any one of the rotor blades or jet engines is damaged. The flying object comprises: a flying fuselage; a plate-shaped protection member having a plurality of through-holes formed on the same circumference thereof; a driving means arranged in each of the through-holes; and a tilting means for tilting each of the driving means, or a rotating means for rotating the protection member around a shaft member, wherein the diameter of the protection member, the interval between the rotational axes of the rotor blades facing each other, the length of the shaft member, and the length of the flying fuselage have a predetermined ratio. | ||||||
| 105 | HYBRID MULTICOPTER AND FIXED WING AERIAL VEHICLE | US16021800 | 2018-06-28 | US20180305008A1 | 2018-10-25 | Jacob Apkarian |
| An aerial vehicle is includes a wing, first and second rotors, and a movement sensor. The first and second multicopter rotors are rotatably coupled to the wing, the first multicopter rotor is rotatable relative to the wing about a first lateral axis, and the second multicopter rotor is rotatable relative to the wing about a second lateral axis. Each multicopter rotor is coupled to each other multicopter rotor, wherein the multicopter rotors are restricted to collective synchronous rotation relative to the wing between a multicopter configuration and a fixed-wing configuration. The movement sensor is coupled to the multicopter rotors, wherein the movement sensor is positioned to rotate relative to the wing when the multicopter rotors rotate relative to the wing between the multicopter and fixed-wing configurations. | ||||||
| 106 | Modular and Morphable Air Vehicle | US15953421 | 2018-04-14 | US20180281944A1 | 2018-10-04 | John W. Piasecki; Frederick W. Piasecki; Brian Geiger; Douglas Johnson; David Pitcairn |
| A personal air vehicle may feature an air module that may be attached to a ground module. The air module may be equipped with exit vanes or vectored engine exhaust to provide redundant control effectors to the cyclic or collective pitch of at least one rotary wing under the control of a control system. | ||||||
| 107 | MULTIROTOR UNMANNED AERIAL VEHICLE | US15730286 | 2017-10-11 | US20180273165A1 | 2018-09-27 | Dalei SONG; Wenbo SU; Tianyu LIN; Zhen ZHANG; Sen MEI |
| The present disclosure relates to a multirotor unmanned aerial vehicle, comprising a fuselage, being provided with at least one support arm in a transverse penetrating manner, and a rotor, being disposed at each end of the support arm in a transverse tilting manner. When the unmanned aerial vehicle moves transversely, the tilting rotors can provide lift force for keeping the unmanned aerial vehicle at certain altitude and also provide power for transverse movement of the unmanned aerial vehicle, and meanwhile, the fuselage does not need to tilt, so that the unmanned aerial vehicle has the advantages of high response rate and high flight speed. | ||||||
| 108 | MULTIROTOR FLYING VEHICLE | US15995377 | 2018-06-01 | US20180273164A1 | 2018-09-27 | David Geise; John Geise |
| A multirotor flying vehicle including at least one rotor support frame organized on a geometric grid, with a plurality of rotor assemblies coupled to the at least one rotor support frame. At least one power supply is coupled to and powers the rotor assemblies. A control system is coupled to the rotor assemblies and is configured to operate the vehicle. | ||||||
| 109 | MAINTAINING ATTITUDE CONTROL OF UNMANNED AERIAL VEHICLES USING PIVOTING PROPULSION MOTORS | US15434836 | 2017-02-16 | US20180229837A1 | 2018-08-16 | Gur Kimchi; Dominic Timothy Shiosaki; Ricky Dean Welsh |
| Aerial vehicles may be configured to control their attitudes by changing one or more physical attributes. For example, an aerial vehicle may be outfitted with propulsion motors having repositionable mounts by which the motors may be rotated about one or more axes, in order to redirect forces generated by the motors during operation. An aerial vehicle may also be outfitted with one or more other movable objects such as landing gear, antenna and/or engaged payloads, and one or more of such objects may be translated in one or more directions in order to adjust a center of gravity of the aerial vehicle. By varying angles by which forces are supplied to the aerial vehicle, or locations of the center of gravity of the aerial vehicle, a desired attitude of the aerial vehicle may be maintained irrespective of velocity, altitude and/or forces of thrust, lift, weight or drag acting upon the aerial vehicle. | ||||||
| 110 | MAINTAINING ATTITUDE CONTROL OF UNMANNED AERIAL VEHICLES BY VARYING CENTERS OF GRAVITY | US15435044 | 2017-02-16 | US20180229833A1 | 2018-08-16 | Gur Kimchi; Dominic Timothy Shiosaki; Ricky Dean Welsh |
| Aerial vehicles may be configured to control their attitudes by changing one or more physical attributes. For example, an aerial vehicle may be outfitted with propulsion motors having repositionable mounts by which the motors may be rotated about one or more axes, in order to redirect forces generated by the motors during operation. An aerial vehicle may also be outfitted with one or more other movable objects such as landing gear, antenna and/or engaged payloads, and one or more of such objects may be translated in one or more directions in order to adjust a center of gravity of the aerial vehicle. By varying angles by which forces are supplied to the aerial vehicle, or locations of the center of gravity of the aerial vehicle, a desired attitude of the aerial vehicle may be maintained irrespective of velocity, altitude and/or forces of thrust, lift, weight or drag acting upon the aerial vehicle. | ||||||
| 111 | Proprotor Systems for Tiltrotor Aircraft | US15355347 | 2016-11-18 | US20180141654A1 | 2018-05-24 | Jouyoung Jason Choi; Gary Miller; Richard Erler Rauber; Thomas Clement Parham, JR.; Alan Carl Ewing; Frank Bradley Stamps |
| A proprotor system for tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub and a plurality of proprotor blades coupled to the hub such that each proprotor blade is operable to independently flap relative to the hub and independently change pitch. In the airplane mode, the proprotor blades have a first in-plane frequency greater than 2.0/rev. | ||||||
| 112 | UNMANNED AERIAL VEHICLE | US15565144 | 2015-07-22 | US20180105266A1 | 2018-04-19 | Seon-Ho LEE |
| A technical object of the present invention is to provide an unmanned aerial vehicle capable of performing a position movement while maintaining posture stabilization. To this end, the unmanned aerial vehicle of the present invention includes: a main body unit; a plurality of propeller motors of which the rotational speed is adjusted by the main body unit; supports which extend from the main body unit in order to support the plurality of propeller motors; propellers which are axially coupled to the plurality of propeller motors and output thrust; and tilting units which tilt rotating shafts of the propellers with respect to the main body unit. | ||||||
| 113 | Hybrid multicopter and fixed wing aerial vehicle | US15585743 | 2017-05-03 | US09873508B2 | 2018-01-23 | Jacob Apkarian |
| An aerial vehicle is includes a wing, first and second rotors, and a movement sensor. The first and second multicopter rotors are rotatably coupled to the wing, the first multicopter rotor is rotatable relative to the wing about a first lateral axis, and the second multicopter rotor is rotatable relative to the wing about a second lateral axis. Each multicopter rotor is coupled to each other multicopter rotor, wherein the multicopter rotors are restricted to collective synchronous rotation relative to the wing between a multicopter configuration and a fixed-wing configuration. The movement sensor is coupled to the multicopter rotors, wherein the movement sensor is positioned to rotate relative to the wing when the multicopter rotors rotate relative to the wing between the multicopter and fixed-wing configurations. | ||||||
| 114 | MULTI-MODE AERIAL VEHICLE | US15195238 | 2016-06-28 | US20170369161A1 | 2017-12-28 | Saeid A. ALZAHRANI |
| A multi-mode aerial vehicle hybrid wing includes a fixed wing configured to extend from a side of an elongated fuselage and double over its longitudinal axis, a tilt wing attached at a first side to a free end of the fixed wing wherein the tilt wing is rotatable ninety degrees about its axis, and a duct attached to a second side of the tilt wing. The duct includes a plurality of pivotal control surfaces positioned at a top entrance of the duct, dual counter-rotating rotors positioned at an underside of the duct, a plurality of cross stators positioned at a back entrance of the duct, and a plurality of stator pivotal control surfaces within each of the cross stators of the duct. The multi-mode aerial vehicle hybrid wing also includes a winglet attached to the duct opposite to the tilt wing. | ||||||
| 115 | Method and apparatus for flight control of tiltrotor aircraft | US11631696 | 2004-07-29 | US09851723B2 | 2017-12-26 | Kenneth E. Builta |
| A method and apparatus provide for automatically controlling the flight of a tiltrotor aircraft while the aircraft is in flight that is at least partially rotor-borne. The method and apparatus provide for automatically tilting nacelles in response to a longitudinal-velocity control signal so as to produce a longitudinal thrust-vector component for controlling longitudinal velocity of the aircraft. Simultaneously, cyclic swashplate controls are automatically actuated so as to maintain the fuselage in a desired pitch attitude. The method and apparatus also provide for automatically actuating the cyclic swashplate controls for each rotor in response to a lateral-velocity control signal so as to produce a lateral thrust-vector component for controlling lateral velocity of the aircraft. Simultaneously, collective swashplate controls for each rotor are automatically actuated so as to maintain the fuselage in a desired roll attitude. The method and apparatus provide for yaw control through differential longitudinal thrust produced by tilting the nacelles. | ||||||
| 116 | HINGE MECHANISM FOR A WEIGHT-SHIFTING COAXIAL HELICOPTER | US15447845 | 2017-03-02 | US20170320565A1 | 2017-11-09 | DUSTIN E. GAMBLE; Matthew Curran; Brian Miller |
| A helicopter includes a gimbal assembly, a first rotor assembly, a second rotor assembly, a fuselage, and a controller. The first rotor assembly, the second rotor assembly, and the fuselage are mechanically coupled to the gimbal assembly. The first rotor assembly includes a first rotor and the second rotor assembly includes a second rotor, the first rotor including a plurality of first fixed-pitch blades and the second rotor including a plurality of second fixed-pitch blades. Each of the plurality of first and the second fixed-pitch blades are coupled to a hub of its respective rotor via a hinge mechanism that is configured to allow each of the fixed-pitch blades to pivot from a first position to a second position, the first position being substantially parallel to the fuselage and the second position being substantially perpendicular to the fuselage. | ||||||
| 117 | HUB SEPARATION IN DUAL ROTOR ROTARY WING AIRCRAFT | US15509741 | 2015-09-28 | US20170297690A1 | 2017-10-19 | Steven D. Weiner; Mikel Brigley; David H. Hunter |
| An aircraft includes an airframe; an extending tail; a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly; and a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe; wherein a ratio of (i) the hub separation between the hub of the upper rotor assembly and the hub of the lower rotor assembly to (ii) a radius of the upper rotor assembly is between about 0.1 and about 0.135. | ||||||
| 118 | MAIN ROTOR ROTATIONAL SPEED CONTROL FOR ROTORCRAFT | US15508346 | 2015-09-29 | US20170283047A1 | 2017-10-05 | Steven D. Weiner; William J. Eadie |
| An aircraft includes an airframe having an extending tail, a counter rotating, coaxial main rotor assembly disposed at the airframe including an upper rotor assembly and a lower rotor assembly and a translational thrust system positioned at the extending tail and providing translational thrust to the airframe. A flight control computer is configured to control a main rotor rotational speed of the upper and the lower rotor assemblies of the main rotor assembly as a function of airspeed of the aircraft. A method of operating an aircraft includes retrieving a threshold main rotor rotational speed of the dual coaxial main rotor assembly and calculating an actual main rotor rotational speed according to an environment of the aircraft. The actual main rotor rotational speed is maintained to remain at or below the threshold main rotor speed according to an airspeed of the aircraft. | ||||||
| 119 | WEIGHT-SHIFTING COAXIAL HELICOPTER | US15085540 | 2016-03-30 | US20170283042A1 | 2017-10-05 | Dustin Eli Gamble |
| A helicopter includes a propulsion system, gimbal assembly, and a controller. The propulsion system includes a first rotor assembly and a second rotor assembly. The first rotor assembly comprises a first motor coupled to a first rotor and the second rotor assembly comprises a second motor coupled to a second rotor. The second rotor is coaxial to the first rotor and is configured to be counter-rotating to the first rotor. The gimbal assembly couples a fuselage of the helicopter to the propulsion system. The controller is communicably coupled to the gimbal assembly and is configured to provide instructions to the gimbal assembly in order to weight-shift the fuselage of the helicopter, thereby controlling movements of the helicopter. | ||||||
| 120 | Gimbaled Tail Rotor Hub with Spherical Elastomeric Centrifugal Force Bearing for Blade Retention and Pitch Change Articulation | US15600229 | 2017-05-19 | US20170259913A1 | 2017-09-14 | Andrew Haldeman; Frank Bradley Stamps; Drew Alan Sutton; James Donn Hethcock |
| A rotor hub comprises a gimbal assembly and an elastomeric centrifugal force bearing. The gimbal assembly is configured to transfer rotational movement of a mast to the rotor hub and to enable the rotor hub to flap relative to the mast. The elastomeric centrifugal force bearing is configured to withstand centrifugal force of a rotor blade when the mast is rotated and is configured to accommodate pitch changes of the rotor blade. A method comprises designing a gimbal assembly that enables a tail rotor hub to flap relative to a tail rotor mast. A centrifugal force bearing is selected that enables tail rotor blades to withstand centrifugal force and that allows for tail rotor blade pitch change articulation. Then, instructions are provided to use the gimbal assembly and the centrifugal force bearing in an in-plane tail rotor assembly. | ||||||
QQ群二维码
意见反馈
意见反馈