| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
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| 141 | 飞行卷笔刀 | CN200710160962.3 | 2007-12-13 | CN101456326A | 2009-06-17 | 陈国兴 |
| 本发明公开了一种飞行卷笔刀，它包括刀体、带刀刀体盖及转杆，带刀刀体盖尾部设有三条伸缩槽，与刀体头部内孔紧凑配合，刀体二边匀称设有二片螺旋桨，刀体尾部圆周中心设有转杆套，转杆套内孔略小于转杆外圆，转杆为椭圆形直纹塑料套管，富有弹性，把其中一段插入转杆套孔内，插入转杆套内的一段转杆既挤成圆柱形，它牢牢的弹在转杆套内，没有一定力度，转杆不会轻易脱离转杆套，装配牢靠。本发明结构合理，装拆方便，既可卷削铅笔，又可以飞行玩。 | ||||||
| 142 | 自稳定旋转玩具 | CN200410005621.5 | 2004-02-15 | CN1618501A | 2005-05-25 | 史提夫·戴维斯 |
| 本发明涉及玩具技术领域，尤其是涉及一种方向无法控制的自稳定旋转玩具。它主要包括有：一个中心座，该中心座具有一根中心轴线和下座体；多个从中心座下部向外延伸的反向旋转上升桨翼，该反向旋转上升桨翼的一个末端与外环相连；一个使中心座和桨翼旋转以产生主要上升力的单一转动装置；中心座的上座体位于反向旋转上升桨翼和转动装置上方以使玩具的重心位于反向旋转上升桨翼之上，从而使玩具获得自稳定效果。本发明仅仅使用一个单一的转动装置配合反向上升桨翼即可使玩具在旋转时产生类似陀螺仪的稳定效果，从而使玩具在飞行旋转具有自稳定效果，性能良好，结构也较为简单。 | ||||||
| 143 | 红外线控擎飞碟 | CN02105105.4 | 2002-02-10 | CN1370615A | 2002-09-25 | 史提夫·戴维斯(StevenDavis) |
| 本发明涉及玩具技术领域,特指一种方向可控型的旋转玩具。其技术方案为:它包括一由内部组件,以及一套设于内部组件上并可相对内部组件做旋转运动的外部组件构成的中心座、至少一个圆形的外环、以及一个带有微处理器的遥控装置,从外部组件向外呈放射状伸出至少三个与外环连接的杆状支架,相邻两个支架之间的夹角相等,每个支架上设置一由马达和螺旋桨构成的旋转装置,从内部组件的下端向下伸出多个具有桨翼的支脚。本发明可完全按操纵者的意图进行方向控制以及不需要使玩具停止转动就能使用降落装置进行着陆。 | ||||||
| 144 | FINGER GYRO SPHERICAL AIRCRAFT | EP23191446.6 | 2023-08-15 | EP4509196A1 | 2025-02-19 | XIE, Guanglong |
A finger gyro spherical aircraft is disclosed according to the present application, including a protective net and a flying body mounted in the protective net, the flying body is provided with an upper shell and a lower shell, the upper shell and the lower shell are assembled to form a mounting cavity, a PCB board, a battery and a motor are mounted in the mounting cavity, the motor has a driving shaft, which extends to an outer end of the upper shell and is connected to a fan blade; the protective net is spherical with a hollow air inlet hole, a top end of the protective net is rotatably provided with a first finger pressing member, a second finger pressing member is rotatably arranged at a bottom end of the protective net.
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| 145 | GANGED SERVO FLIGHT CONTROL SYSTEM FOR AN UNMANNED AERIAL VEHICLE | EP22152835.9 | 2016-08-25 | EP4026771A1 | 2022-07-13 | HOLLY, Lance; DONOVAN, Lawrence |
A ganged servo flight control system for an unmanned aerial vehicle is provided. The flight control system may include a swashplate having first, second, and third connection portions; a first control assembly connected to the first connection portion of the swashplate; a second control assembly connected to the second connection portion of the swashplate; and a third control assembly connected to the third connection portion of the swashplate. The first control assembly may include two or more servo-actuators connected to operate in cooperation with each other.
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| 146 | AN AERODYNAMIC LIFTING DEVICE | EP14820445.6 | 2014-06-30 | EP3016727B1 | 2018-12-19 | SCHLUNKE, Kim Christopher; SEEBER, Ken; LAMB, Rodney |
| 147 | GIMBALED THRUSTER CONFIGURATION FOR USE WITH UNMANNED AERIAL VEHICLE | EP16867252.5 | 2016-11-18 | EP3380397A1 | 2018-10-03 | LUKACZYK, Trent; COLONNO, Michael |
A vectored thrust control module for an aircraft that includes a servo system that couples to the aircraft structure at an output shaft connection point. A thrust motor assembly is fully supported by the servo system and rotates a bladed component to provide thrust to the aircraft. Further, the thrust motor assembly is rigidly connected with the servo system to rotate together about a longitudinal axis thrust line with respect to the aircraft structure. The bladed component and the thrust motor assembly generate a line of thrust that extends through the connection point of the servo system to the aircraft structure.
A vectored thrust control module for an aircraft that includes a servo system that couples to the aircraft structure at an output shaft connection point. A thrust motor assembly is fully supported by the servo system and rotates a bladed component to provide thrust to the aircraft. Further, the thrust motor assembly is rigidly connected with the servo system to rotate together about a longitudinal axis thrust line with respect to the aircraft structure. The bladed component and the thrust motor assembly generate a line of thrust that extends through the connection point of the servo system to the aircraft structure. |
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| 148 | AN UNMANNED AERIAL VEHICLE | EP13900333.9 | 2013-12-24 | EP3087003A1 | 2016-11-02 | CHAN, Keen Ian |
| An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method of assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises an elongated wing structure having an elongated axis along the longest dimension of the elongated wing structure, the elongated wing structure having a middle location at a substantially halfway point; a connecting structure extending substantially perpendicularly from the elongated wing structure, the connecting structure being offset from the middle location of the elongated wing structure at a first position along the elongated axis; and at least three sets of propellers, wherein at least two sets of propellers are mounted on the connecting structure, and wherein at least one set of propellers is mounted at a second position offset from the middle location in an opposite direction away from the connecting structure. | ||||||
| 149 | Self-righting frame and aeronautical vehicle | EP12165691.2 | 2012-04-26 | EP2517767A2 | 2012-10-31 | Dees, James; Yan, Gaofei |
An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has a protrusion extending upwardly from a central vertical axis. The protrusion provides an initial instability to begin a self-righting process when the aeronautical vehicle is inverted on a surface. A propulsion system, such as rotor driven by a motor can be mounted in a central void of the self-righting frame assembly and oriented to provide a lifting force. A power supply is mounted in the central void of the self-righting frame assembly and operationally connected to the at least one rotor for rotatably powering the rotor. An electronics assembly is also mounted in the central void of the self-righting frame for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a surface.
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| 150 | DIRECTIONALLY CONTROLLABLE FLYING VEHICLE AND A PROPELLER MECHANISM FOR ACCOMPLISHING THE SAME | EP09730710.2 | 2009-03-30 | EP2285460A4 | 2012-06-06 | Davis, Steven |
| 151 | BOOMERANG | EP08837414.5 | 2008-10-09 | EP2219752A4 | 2011-12-21 | HO, Vinh Hoang |
| 152 | Helicopter | EP09170748.9 | 2009-09-18 | EP2298645A1 | 2011-03-23 | van de Rostyne, Alexander Jozef Magdalena; Wai, Chi Pok Billy |
A helicopter includes a system to effect motion in a horizontal dimension thereby to direct the desired direction. The rotor blades are driven by a rotor shaft and which is hinge mounted on this rotor shaft, such that the angle between the plane of rotation of the main rotor and the rotor shaft may vary. A control for moving the angle of incidence of at least one blade of the rotor cyclically along at least part of a 360-degree rotation path around the rotor shaft. This causes a variation in a lift force of the blade along at least part of the rotations path. This causes the body to be urged in a relatively horizontal direction from a relative position of rest. The control includes an actuator for engaging with an assembly depending from the rotor, the inter-engagement of the actuator and assembly effecting a change in the angle of incidence of at least the one blade of the rotor. The system includes a rotor, preferably complemented with a stabilizer rotor. There is a control ring attached to the main rotor, and an actuator device connected with the helicopter body structure. The control ring is generally centered around the vertical rotor axis, and moves with the rotor when tilted around the feather axis.
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| 153 | DIRECTIONALLY CONTROLLABLE FLYING VEHICLE AND A PROPELLER MECHANISM FOR ACCOMPLISHING THE SAME | EP09730710.2 | 2009-03-30 | EP2285460A1 | 2011-02-23 | Davis, Steven |
| A flying vehicle in accordance to an embodiment of the present invention includes a propeller control mechanism for flying the vehicle. The propeller control mechanism includes a propeller having a center shaft for connecting to the drive shaft; first and second propeller blades extending from the center shaft; and a control mechanism including a first linkage connecting the center shaft to the first propeller blade and a second linkage connecting the center shaft to a region defined on the propeller, wherein a change in a driving torque of the drive shaft causes the first linkage and the second linkage to change the pitch and height of the propeller blades while substantially unchanging the tip path plane of the propeller blades. | ||||||
| 154 | Flugkreisel | EP01104707.3 | 2001-02-26 | EP1127600A3 | 2003-11-19 | Eckert, Wolfgang |
Die Erfindung richtet sich auf ein Spielgerät in Form eines Flugkreisels, bestehend aus einem flächigen Körper mit wenigstens einem schwerpunktnahen Bereich und wenigstens einem Fortsatz, der ein freies Ende aufweist, und auf ein Verfahren zum Starten desselben, wobei der flache Körper mit seinem schwerpunktnahen Bereich auf eine konvex gewölbte Oberfläche, insbesondere einen Fingerknöchel od. dgl., gelegt wird und sodann mit einem Finger etwa horizontal und tangential gegen das freie Ende eines Fortsatzes geschnippt wird, um den flachen Körper in eine schnelle Rotationsbewegung ω (ω ≥ 300 U/min) bei gleichzeitig langsamer Translationsbewegung vT (vT ≤ ω * r) zu versetzen, so dass dieser eine die Lage stabilisierende Kreiselkraft erfährt, dadurch horizontal ausgerichtet bleibt und aufgrund seiner flächigen Gestalt während seines Fluges von einem Luftkissen getragen wird. |
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| 155 | FINGER FLYING HOVER TOY | PCT/US2018/049002 | 2018-08-31 | WO2019050783A1 | 2019-03-14 | PARKER, D.; PARKER, Jt; PARKER, Jd |
A flying toy system capable of independently hovering at a programmable height and respond to the manipulations and/or actions of one or more users through their fingers or similar digit extensions, all while continuing an autonomous flight regime. |
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| 156 | ASYMMETRIC AERIAL VEHICLE | PCT/SG2017/050356 | 2017-07-18 | WO2019017833A1 | 2019-01-24 | CHAN, Keen Ian |
An aerial vehicle including a first wing structure and a second wing structure which intersects the first wing structure perpendicularly at a position offset from a midpoint of a transverse axis of the first wing structure in a direction towards a first wingtip of the first wing structure. The aerial vehicle may further include a first set of at least two propellers with respective propeller rotational axes disposed side-by-side along a portion of the first wing structure extending between the midpoint of the transverse axis of the first wing structure and a second wingtip of the first wing structure. The aerial vehicle may further include a second set of at least two propellers with respective propeller rotational axes disposed side-by-side along a first portion of the second wing structure extending from a first surface of the first wing structure. The aerial vehicle may further include a third set of at least two propellers with respective propeller rotational axes disposed side-by-side along a second portion of the second wing structure extending from a second surface of the first wing structure. |
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| 157 | AERIAL VEHICLE | PCT/SG2017/050241 | 2017-05-09 | WO2018208220A1 | 2018-11-15 | CHAN, Keen Ian |
An aerial vehicle may include a first wing structure. The aerial vehicle may further include a first propeller and a second propeller disposed along the first wing structure. The aerial vehicle may further include a second wing structure disposed to intersect the first wing structure to form a cross configuration. The aerial vehicle may further include a third propeller and a fourth propeller disposed along the second wing structure. In a hovering orientation of the aerial vehicle, respective propeller rotational axes of the first and second propellers may be angled off-vertical in respective planes which may be perpendicular to a transverse axis of the first wing structure, and respective propeller rotational axes of the third and fourth propellers may be angled off-vertical in respective planes which may be perpendicular to a transverse axis of the second wing structure. |
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| 158 | HYBRID MULTICOPTER AND FIXED WING AERIAL VEHICLE | PCT/CA2016/051438 | 2016-12-08 | WO2017096478A1 | 2017-06-15 | APKARIAN, Jacob |
An aerial vehicle is disclosed which includes a body and a multicopter. The body has at least one wing. The multicopter is rotatably mounted to the body about a multicopter axis. The multicopter includes a plurality of rotors positioned and controllable to rotate the multicopter about the multicopter axis. |
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| 159 | AN UNMANNED AERIAL VEHICLE | PCT/SG2013/000548 | 2013-12-24 | WO2015099603A1 | 2015-07-02 | CHAN, Keen Ian |
An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method of assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises an elongated wing structure having an elongated axis along the longest dimension of the elongated wing structure, the elongated wing structure having a middle location at a substantially halfway point; a connecting structure extending substantially perpendicularly from the elongated wing structure, the connecting structure being offset from the middle location of the elongated wing structure at a first position along the elongated axis; and at least three sets of propellers, wherein at least two sets of propellers are mounted on the connecting structure, and wherein at least one set of propellers is mounted at a second position offset from the middle location in an opposite direction away from the connecting structure. |
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| 160 | ROTORCRAFT WITH INTEGRATED LIGHT PIPE SUPPORT MEMBERS | PCT/US2014/051361 | 2014-08-15 | WO2015023992A1 | 2015-02-19 | CHRISTENSEN, Casey Christen Jens; ALLMENDINGER, Otto, Karl; HOHNHOLT, Richard Douglas; POTEET, Kent; SCHMITZ, Scott Rollin Michael; BLACKWELL, Thomas |
A radio controlled model rotorcraft implemented with features improving ease of flight and flight performance by increasing structural stability, increasing rotorcraft visibility and orientation awareness through the use of multifunctioning, configurable, and aesthetically pleasing components, while also increasing resistance to damage from crashes through use of impact and vibration absorbing components. |
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