| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 便携式无人机、桨叶转动组件、转动系统及其组装方法 | CN201710391767.5 | 2017-05-27 | CN107187590A | 2017-09-22 | 田瑜; 江文彦; 朱小刚 |
| 本发明涉及一种便携式无人机、桨叶转动组件、转动系统及其组装方法。所述桨叶转动组件包括桨座、桨叶和连接轴，所述桨座上设有贯通的第一连接孔，所述桨叶上设有贯通的第二连接孔，所述连接轴穿设于第一、二连接孔，并分别与第一连接孔螺纹配合以及与第二连接孔间隙配合。所述转动系统包括桨叶转动组件以及与桨座和连接轴连接的电机。所述便携式无人机包括可折叠的机身以及与机身连接的多个转动系统。本发明简化了便携式无人机在组装以及更换维护时的操作过程。 | ||||||
| 2 | 一种直升机旋翼挥舞铰 | CN201610152945.4 | 2016-03-17 | CN105620742A | 2016-06-01 | 赵青; 王健; 张昊; 邬文强 |
| 本发明公开了一种直升机旋翼挥舞铰，涉及直升机技术领域。所述直升机旋翼挥舞铰，安装在旋翼轴(9)上，包含套环(1)、两块夹板(2)及两个滚动轴承(3)，其中，所述套环(1)套设在旋翼轴(9)上，并随旋翼轴(9)转动，套环(1)的圆周外侧相隔180度设置有轴承安装段(11)；所述两块夹板(1)通过滚动轴承(3)设置在所述轴承安装段(11)上，所述滚动轴承(3)的轴线与所述旋翼轴(9)的轴线垂直，两块夹板(2)通过连接件固定连接。本发明的有益效果在于：本发明的两块夹板通过滚动轴承设置在所述轴承安装段上，两块夹板通过连接件固定连接，夹板通过滚动轴承绕套环摆动，套环与夹板不易磨损，挥舞铰使用寿命更长。 | ||||||
| 3 | 一种可变直径的旋翼及其飞行器 | CN201610031890.1 | 2016-01-15 | CN105523181A | 2016-04-27 | 何春旺 |
| 本发明涉及一种可变直径的旋翼及其飞行器，该旋翼包括驱动轴、桨毂和至少两个的桨叶，桨毂安装于驱动轴的顶端，桨叶均匀分布的安装于桨毂外周围；桨毂上铰接有摆动块，桨毂内的每个摆动块上还连接有限定偏转摆动量大小控制每个桨叶直径变动量范围的弹性偏压装置；使得桨榖在驱动轴驱动下转动时，桨叶受离心力影响会沿桨毂径向向外移动，从而使旋翼直径变大，速度越高所受离心力越大，向外张开的程度越大，旋翼产生的动力越大；在桨叶速度变小时，桨叶在弹性偏压装置的回复力作用下向内收缩，使旋翼直径变小，旋翼产生的动力变小，实现对桨叶速度调节的同时对旋翼直径也进行了调节，使旋翼对动力调节的反应速度加快，动力的可调节范围增大。 | ||||||
| 4 | 具有稳定器装置的旋翼机 | CN201510783484.6 | 2015-09-18 | CN105460205B | 2017-06-13 | P·艾格林 |
| 本发明涉及具有横尾翼(15)和/或尾翼(20)型的至少一个稳定器装置(10)的旋翼机(1)。至少一个稳定器装置(10)是可变翼面积稳定器装置(11)，该装置包含提供有固定翼面(31)和可移动翼面(35)的机翼部件(30)。控制系统(50)连接到移动系统(40)，移动系统(40)用于在缩回位置(POS1)和展开位置之间平移所述可移动翼面(35)，当旋翼机具有低于第一速度阈值(110)的向前速度(IAS)时可移动翼面(35)占据缩回位置(POS1)，当旋翼机(1)具有比高于第一速度阈值(110)的第二速度阈值(120)更高的向前空气速度(IAS)时可移动翼面(35)占据展开位置。 | ||||||
| 5 | 具有稳定器装置的旋翼机 | CN201510783484.6 | 2015-09-18 | CN105460205A | 2016-04-06 | P·艾格林 |
| 本发明涉及具有横尾翼(15)和/或尾翼(20)型的至少一个稳定器装置(10)的旋翼机(1)。至少一个稳定器装置(10)是可变翼面积稳定器装置(11)，该装置包含提供有固定翼面(31)和可移动翼面(35)的机翼部件(30)。控制系统(50)连接到移动系统(40)，移动系统(40)用于在缩回位置(POS1)和展开位置之间平移所述可移动翼面(35)，当旋翼机具有低于第一速度阈值(110)的向前速度(IAS)时可移动翼面(35)占据缩回位置(POS1)，当旋翼机(1)具有比高于第一速度阈值(110)的第二速度阈值(120)更高的向前空气速度(IAS)时可移动翼面(35)占据展开位置。 | ||||||
| 6 | 旋翼飞行器的旋翼系统 | CN201410282878.9 | 2014-06-23 | CN104229135A | 2014-12-24 | K·冯-威尔默斯基 |
| 一种旋翼飞行器的旋翼系统，诸如直升飞机之类的飞行器，该旋翼系统具有旋翼主轴、旋翼毂(1)、至少四个角向基本上均匀分布的旋翼桨叶(2、3)及用于桨距和随后拍动控制的倾斜盘支撑件(15)。桨叶分别相对于彼此零偏移地、以不易摆振且拍动的方式成对安装于具有中空支承件(20)的旋翼毂，支承件其内部有至少一个附加支承件(21)，第一对旋翼桨叶安装在可沿基本上垂直于转动轴线的第一拍动方向(23)枢转的支承件中，第二对旋翼桨叶在支承件内部安装在内部附加支承件上，内部附加支承件可沿第二拍动方向(22)且独立于第一对旋翼桨叶枢转，第二拍动方向基本上垂直于第一拍动方向及转动轴线。该旋翼系统构造复杂性低、更具成本效率且可靠性高。 | ||||||
| 7 | 旋翼机头、旋翼机及旋翼机的提升方法 | CN201710723920.X | 2017-08-22 | CN107344617A | 2017-11-14 | 胡礼杰; 郑尧刚; 徐淑芹 |
| 本发明提供了一种旋翼机头、旋翼机及旋翼机的提升方法，属于飞行器技术领域。旋翼机头包括机架、主轴、第一连接件、旋翼夹持件、倾斜盘、第二连接件和操纵连接件。主轴可转动的连接于机架；第一连接件与主轴连接；旋翼夹持件可转动的连接于第一连接件，且旋翼夹持件的转动轴心线与主轴的转动轴心线垂直设置；倾斜盘包括第一盘和第二盘，第一盘与主轴连接且随主轴的转动而转动，第一盘沿主轴的转动轴心线可滑动，第二盘与机架连接且用于控制第一盘；第二连接件的一端与旋翼夹持件连接，第二连接件的另一端与第一盘连接；操纵连接件与机架连接且用于控制第二盘。旋翼机选用该旋翼机头，其不需要较长的跑道就可以实现提升，整体使用效果较佳。 | ||||||
| 8 | 旋翼飞行器的旋翼系统 | CN201410282878.9 | 2014-06-23 | CN104229135B | 2016-08-31 | K·冯-威尔默斯基 |
| 一种旋翼飞行器的旋翼系统，诸如直升飞机之类的飞行器，该旋翼系统具有旋翼主轴、旋翼毂(1)、至少四个角向基本上均匀分布的旋翼桨叶(2、3)及用于桨距和随后拍动控制的倾斜盘支撑件(15)。桨叶分别相对于彼此零偏移地、以不易摆振且拍动的方式成对安装于具有中空支承件(20)的旋翼毂，支承件其内部有至少一个附加支承件(21)，第一对旋翼桨叶安装在可沿基本上垂直于转动轴线的第一拍动方向(23)枢转的支承件中，第二对旋翼桨叶在支承件内部安装在内部附加支承件上，内部附加支承件可沿第二拍动方向(22)且独立于第一对旋翼桨叶枢转，第二拍动方向基本上垂直于第一拍动方向及转动轴线。该旋翼系统构造复杂性低、更具成本效率且可靠性高。 | ||||||
| 9 | 具有控制机构的等速万向节 | CN201310553025.X | 2013-11-08 | CN103807309B | 2016-08-17 | 德鲁·A·萨顿; 克里斯托弗·福斯基; 达德利·史密斯; 弗兰克·B·斯坦普斯 |
| 根据一种实施方式，等速(CV)万向节包括第一轭部、第二轭部以及控制机构。第一轭部构造为围绕第一轴线可旋转地与输入设备联接并且构造为通过第一开口容纳输入设备。第二轭部围绕第二轴线可旋转地与第一轭部联接并且围绕第三轴线可旋转地与输出设备联接。控制机构适于约束第一轭部和第二轭部，以便实现输入设备与输出设备之间的基本CV(等速的)特征。 | ||||||
| 10 | 具有控制机构的等速万向节 | CN201310553025.X | 2013-11-08 | CN103807309A | 2014-05-21 | 德鲁·A·萨顿; 克里斯托弗·福斯基; 达德利·史密斯; 弗兰克·B·斯坦普斯 |
| 根据一种实施方式，等速(CV)万向节包括第一轭部、第二轭部以及控制机构。第一轭部构造为围绕第一轴线可旋转地与输入设备联接并且构造为通过第一开口容纳输入设备。第二轭部围绕第二轴线可旋转地与第一轭部联接并且围绕第三轴线可旋转地与输出设备联接。控制机构适于约束第一轭部和第二轭部，以便实现输入设备与输出设备之间的基本CV(等速的)特征。 | ||||||
| 11 | 복합 매트릭스 재료의 바 | KR1020140032890 | 2014-03-20 | KR1020140118797A | 2014-10-08 | 팔러루페르트; 바그너볼프강제이.; 오트너마틴 |
| A bar (1) of a composite matrix material in a rotary-wing aircraft has a longitudinal shaft (8) which is vertical to a cross section having an upper surface (2) and a lower surface (3). At least one torsion box (17) includes upper layers and under layers (10, 21, 11, 22) offset from the shaft (8), the upper surface (2), and the lower surface (3). The upper and lower layers (10, 21, 11, 22) are combined horizontally whereas the cross sections are filled with a first group of fibers extending fundamentally being in parallel with the shaft (8). | ||||||
| 12 | DRONE | US16322557 | 2017-07-26 | US20190248492A1 | 2019-08-15 | Sylvain ROLDAN DE PERERA |
| An assembly comprising a drone (1) and at least one releasable load (37) mounted on the drone, the drone comprising an on-board data processing system, the releasable load (37) comprising at least one sensor delivering a piece of information that can be used to ascertain the path of same and actuators for controlling flight control surfaces allowing it to be oriented as it falls, being linked to the drone (1) by an optical fibre (70), the load and the drone being arranged to exchange information via the optical fibre while the load is falling, the load transmitting data originating from said at least one sensor and the drone transmitting data for controlling the actuators, established taking into account that received from the load, in order to guide the load towards a predefined target. | ||||||
| 13 | PITCH BEARING ASSEMBLY FOR ROTOR SYSTEM AND AIRCRAFT | US15902122 | 2018-02-22 | US20180305006A1 | 2018-10-25 | Ryan Lehto; Robert D Higbie; James Everett McCollough; Joshua R. Richards; Bryan Kenneth Baskin |
| A pitch bearing assembly includes an inboard pitch bearing including an inner race and an outer race, the outer race including a radially outwardly protruding tab, and an outboard end of the inboard pitch bearing including a plurality of rotation transmitting features. An outboard pitch bearing of the pitch bearing assembly includes an inner race and an outer race, an inboard end of the outer race of the outboard pitch bearing including a plurality of rotation transmitting features. A coupler of the pitch bearing assembly has an inboard end and an outboard end, the inboard end of the coupler having a plurality of rotation transmitting features engageable with the rotation transmitting features of the inboard pitch bearing, the outboard end of the coupler having a plurality of rotation transmitting features engageable with the rotation transmitting features of the outboard pitch bearing. | ||||||
| 14 | Rotor hub for a rotorcraft | US14135941 | 2013-12-20 | US09896199B2 | 2018-02-20 | Christopher Foskey; Drew Sutton; Frank B. Stamps |
| A rotor hub can include a yoke, a mast, and one or more radially oriented actuators. The first radial actuator and the second radial actuator each have a piston configured to impart a translation of the yoke relative to the mast. The radial actuators are configured to attenuate in-plane whirling vibrations. The rotor hub can also have actuators coupled between the mast and the yoke for attenuating flapping and vertical vibrations. | ||||||
| 15 | RECONFIGURABLE UNMANNED AIRCRAFT SYSTEM | US14560606 | 2014-12-04 | US20160272310A1 | 2016-09-22 | ALISTAIR K. CHAN; JESSE R. CHEATHAM, III; HON WAH CHIN; WILLIAM DAVID DUNCAN; RODERICK A. HYDE; MURIEL Y. ISHIKAWA; JORDIN T. KARE; TONY S. PAN; ROBERT C. PETROSKI; CLARENCE T. TEGREENE; DAVID B. TUCKERMAN; THOMAS ALLAN WEAVER; LOWELL L. WOOD, JR. |
| A reconfigurable unmanned aircraft system is disclosed. A system and method for configuring a reconfigurable unmanned aircraft and system and method for operation and management of a reconfigurable unmanned aircraft in an airspace are also disclosed. The aircraft is selectively reconfigurable to modify flight characteristics. The aircraft comprises a set of rotors. The position of at least one rotor relative to the base can be modified by at least one of translation of the rotor relative to the boom, pivoting of the boom relative to the base, and translation of the boom relative to the base; so that flight characteristics can be modified by configuration of position of at least one rotor relative to the base. A method of configuring an aircraft having a set of rotors on a mission to carry a payload comprises the steps of determining properties of the payload including at least mass properties, determining the manner in which the payload will be coupled to the aircraft, determining configuration for each of the rotors in the set of rotors at least partially in consideration of the properties of the payload, and positioning the set of rotors in the configuration for the aircraft to perform the mission. | ||||||
| 16 | Constant velocity joint with control mechanism | US13673475 | 2012-11-09 | US09399513B2 | 2016-07-26 | Drew A. Sutton; Christopher Foskey; Dudley Smith; Frank B. Stamps |
| According to one embodiment, a constant velocity (CV) joint includes a first yoke, a second yoke, and a control mechanism. The first yoke is configured to be rotatably coupled to an input device about a first axis and configured to receive the input device through a first opening. The second yoke is rotatably coupled to the first yoke about a second axis and rotatably coupled to an output device about a third axis. The control mechanism is adapted to constrain the first yoke and the second yoke so as to achieve a substantially CV characteristic between the input device and the output device. | ||||||
| 17 | Rotor blade coupling device and rotor head | US13405649 | 2012-02-27 | US09090344B2 | 2015-07-28 | Martin Stucki |
| A rotor blade coupling device (9) comprising a torsionally rigid carrier (4) is disclosed, the carrier (4) being mounted in a manner which is free of centrifugal force between a thrust bearing (3) and a control bearing (5), resilient impact and pivoting movements of the rotor blade coupling device (9) being able to take place in a damped manner. The rotor blade coupling device (9) is clamped between a rotor head star (101) and a rotor head central piece (102) and held rotatably about the rotor axis A. The centrifugal forces which occur, are transmitted from a rotor blade holder (2) to the rotor head star (101) and thus kept away from the carrier (4). | ||||||
| 18 | ROTOR HUB FOR A ROTORCRAFT | US14135941 | 2013-12-20 | US20150175259A1 | 2015-06-25 | Christopher Foskey; Drew Sutton; Frank B. Stamps |
| A rotor hub can include a yoke, a mast, and one or more radially oriented actuators. The first radial actuator and the second radial actuator each have a piston configured to impart a translation of the yoke relative to the mast. The radial actuators are configured to attenuate in-plane whirling vibrations. The rotor hub can also have actuators coupled between the mast and the yoke for attenuating flapping and vertical vibrations. | ||||||
| 19 | Constant Velocity Joint with Control Mechanism | US13673475 | 2012-11-09 | US20140133979A1 | 2014-05-15 | Drew A. Sutton; Christopher Foskey; Dudley Smith; Frank B. Stamps |
| According to one embodiment, a constant velocity (CV) joint includes a first yoke, a second yoke, and a control mechanism. The first yoke is configured to be rotatably coupled to an input device about a first axis and configured to receive the input device through a first opening. The second yoke is rotatably coupled to the first yoke about a second axis and rotatably coupled to an output device about a third axis. The control mechanism is adapted to constrain the first yoke and the second yoke so as to achieve a substantially CV characteristic between the input device and the output device. | ||||||
| 20 | Coupled aircraft rotor system | US10053312 | 2002-01-18 | US20020134883A1 | 2002-09-26 | Frank B. Stamps; James L. Braswell JR.; David A. Popelka; Richard L. Bennett; Thomas B. Settle JR.; Charles E. Covington; Cecil E. Covington; Peggy Covington |
| An aircraft with a tilt rotor assembly comprising a craft body, a plurality of rotor blades which are subject to three modes of flight operation, a tilting mast coupling the plurality of rotor blades to the craft body and for selectively moving the plurality of rotor blades between the three modes of flight operation, a hub coupling the plurality of rotor blades to the tilting mast in a manner which transfers torque and thrust while allowing tilting of a rotor thrust vector, a main swashplate for tilting in response to operator input to control the direction of the rotor thrust vector, a plurality of pitch horns, each mechanically coupled to a particular one of the plurality of rotor blades and to the main swashplate, for communicating swashplate input to each of the plurality of rotor blades, a plurality of links coupling the main swashplate to the plurality of pitch horns, wherein each of the plurality of pitch horns is mechanically coupled to a particular one of the plurality of rotor blades by one of the plurality of links in a particular position which yields a delta-3 value which is not optimum, and a feedback swashplate and cooperating feedback links for receiving disk tilting input from the plurality of rotor blades during flight, and for supplying a mechanical input to the main swashplate to compensate for the less than optimum delta-3 coupling between the plurality of pitch horns and the plurality of links. The three modes of flight include: (1) an airplane mode of flight with the plurality of rotor blades in a rotor disk position which is substantially transverse to the craft body; (2) a helicopter mode of flight with the plurality of rotor blades in a rotor disk position substantially parallel to the craft body with direction of flight being controlled by a rotor thrust vector; and (3) a transition mode of flight with the plurality of rotor blades moving between the rotor disk positions associated with the airplane mode of flight and the helicopter mode of flight. | ||||||
QQ群二维码
意见反馈
意见反馈