| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 21 | Propeller sound alteration for a drone | US15194317 | 2016-06-27 | US10023298B1 | 2018-07-17 | Brian C. Beckman; Michael Rolnik |
| Techniques for using an unmanned aerial vehicle (UAV) to deliver a payload while reducing and/or altering sound generated by the UAV during delivery may be provided. For example, during delivery, the UAV may be instructed to utilize one or more sets of propellers of different sizes to reduce and/or alter the sound generated by and/or around the UAV. Intrinsic and extrinsic information associated with the UAV may be utilized to dynamically adjust the particular sets of propellers of a certain and different size to utilize during different portions of a flight path while delivering the payload. | ||||||
| 22 | Drone noise reduction | US15194258 | 2016-06-27 | US10023297B1 | 2018-07-17 | Brian C. Beckman; Michael Rolnik |
| Techniques for using an unmanned aerial vehicle (UAV) to deliver a payload while reducing and/or altering sound generated by the UAV during delivery may be provided. For example, during delivery, the UAV may be instructed to utilize one or more sets of propellers of different sizes to reduce and/or alter the sound generated by and/or around the UAV. Intrinsic and extrinsic information associated with the UAV may be utilized to dynamically adjust the particular sets of propellers of a certain and different size to utilize during different portions of a flight path while delivering the payload. | ||||||
| 23 | Collapsible airfoil spooled retractable rotor | US14517641 | 2014-10-17 | US09586674B2 | 2017-03-07 | Kenneth A. Cote |
| A retractable rotor system for an aircraft includes a rotor blade with a leading edge, a trailing edge, and an internal collapsible web. The leading edge includes a flexible portion whose lower edge contacts but is not structurally joined to the lower skin. When the leading edge is peeled forward from the lower skin, the blade elastically collapses to the thickness of its constituent layers. The rotor blade extends through a support frame connectable to the aircraft to secure the rotor blade to a spool. Rotating the spool retracts the rotor blade through the support frame while pulling the rotor blade over a fixed actuating member, placing the rotor blade in the collapsed condition and winding the rotor blade onto the spool. Rotating the spool in the opposite direction unwinds the rotor blade from the spool, through the frame, causing the rotor blade to relax into the expanded condition. | ||||||
| 24 | A DRONE | US15304220 | 2015-04-15 | US20170036761A1 | 2017-02-09 | Philippe CROCHAT |
| A drone with a horizontal rotor includes one or more rotor(s) (115, 116) which rotate in a horizontal plane, each rotor (115, 116) being equipped with one or more rigid or non-rigid blades (120, 121), the blade end being mounted on an electric motor (110, 111) with a propeller. | ||||||
| 25 | Propeller arrangement | US13027653 | 2011-02-15 | US08770935B2 | 2014-07-08 | Alexander V. Lavrenko |
| A propeller arrangement has a first propeller assembly providing a row of first propellers, and a second propeller assembly, rearward of the first propeller assembly, providing a row of second propellers. The first and second propellers are radially extendable and retractable. The propeller arrangement further has a control system for controlling the extension and retraction of the first and second propellers. The control system is arranged such that when the propellers of one of the first and second propeller assemblies extend, the propellers of the other of the first and second assemblies retract. | ||||||
| 26 | TURBINE ENGINE HAVING TWO UNDUCTED PROPELLERS | US13810833 | 2011-07-13 | US20130115083A1 | 2013-05-09 | Alexandre Alfred, Gaston Vuillemin |
| A turbine engine including two outer coaxial counter-rotating unducted propellers, of an upstream propeller and a downstream propeller, respectively. The blades of the downstream propeller are retractable in the lengthwise direction thereof so as to reduce the diameter of the propeller. The reduction in the diameter of the downstream propeller makes it possible to reduce noise caused by vortices generated by the upstream propeller. | ||||||
| 27 | DISC ROTOR RETRACTION SYSTEM | US13037205 | 2011-02-28 | US20120219417A1 | 2012-08-30 | Daniel M. Podgurski |
| A disc rotor blade retraction system includes a main blade spar incorporating a hydraulic cylinder and having a screw thread, A ball screw is concentrically carried within the main blade spar and is operably connected to a ball nut which has an outboard end connected to an intermediate spar with a hydraulic piston received for reciprocation in the hydraulic cylinder. A first geared actuator engages the ball screw and a second geared actuator engages the main blade spar screw thread. A hydraulic fluid accumulator providing pressurized hydraulic fluid is connected to an outboard end of the hydraulic cylinder and a controller actuates the first and second geared actuators. | ||||||
| 28 | Variable-Diameter Rotor with Centrifugal Forces Compensation Mechanism | US12624825 | 2009-11-24 | US20100150717A1 | 2010-06-17 | Raul Turmanidze; Malkhaz Chkoidze; Nodari Jojua |
| A variable-diameter rotor comprises a hub with a shaft and rotor blades, wherein each of the rotor blades comprises a radially internal blade part and a radially external blade part. In each of the rotor blades, a jackscrew mechanism is arranged therein and includes a jackscrew arranged in the radially internal blade part and a nut connected with the radially external blade part, the nut cooperating with the jackscrew for radially moving the radially external blade part with respect to the radially internal blade part. The rotor further comprises an energy storage system, including a compressed-gas accumulator. The compressed-gas accumulator comprises a volume of gas and a piston for compressing and expanding the volume of pressurized gas. The energy storage system also includes a means for converting a radial motion of the radially external blade part into a motion of the piston of the compressed-gas accumulator and vice-versa. | ||||||
| 29 | Methods and apparatus for adjustable surfaces | US12181490 | 2008-07-29 | US07728267B2 | 2010-06-01 | Terry M. Sanderson; Jamie W. Clark |
| Methods and apparatus for systems having deployable elements according to various aspects of the present invention comprise a system including a deployable surface and an adaptive actuator including a polymer foam. In one embodiment, the system comprises a vehicle including a deployable wing comprising an exterior surface. The exterior surface may be adjusted by adjusting the shape, size, position, and/or orientation of the adaptive actuator. | ||||||
| 30 | Torque tube/spar assembly for variable diameter helicopter rotors | US412175 | 1995-03-28 | US5636969A | 1997-06-10 | David G. Matuska; Edward W. Gronenthal; W. Donald Jepson |
| A torque tube/spar assembly (100) for transferring operational loads of a Variable Diameter Rotor blade assembly (16) to a rotor hub assembly (18) and includes a torque tube member (24), a spar member (30) and a bearing assembly (40a, 40b) for telescopically mounting the spar member (30) to the torque tube member (24) and furthermore defines an internal channel (62) for housing a retraction/extension mechanism (64) which mounts to an internally formed restraint surface (86) of the spar member (30) and is operative to vary the length of the rotor blade assembly (18). The torque tube member (30) has a substantially constant external geometry along the length of bearing assembly engagement and defines a root end region (102), a tip end region (106) and an intermediate transition region (104) disposed therebetween. The spar member (30) has a substantially constant internal geometry and defines a root end region (110), a first transition (112), an intermediate region (114), a second transition region (116), a restraint region (118) and a tip end region (120). Each of the various regions of the torque tube and spar members (24, 30) have a characteristic stiffness value wherein the characteristic values (104m, 106m) of the intermediate transition and tip end regions (104,106) of the torque tube member (24) are less than the characteristic stiffness value (102m) of the root end region (102) thereof, and wherein the characteristic stiffness value (118m) of the restraint region (118) of the spar member (30) is greater than said characteristic stiffness values (114m, 120m) of the intermediate and tip end regions (114, 120) thereof, and wherein the characteristic stiffness value (114m) of the intermediate region (114) is less than the characteristic stiffness values (110m, 112m, 116m, 118m) of the root end, first transition, second transition and restraint regions (110, 112, 116, 118). | ||||||
| 31 | Drive system for changing the diameter of a variable diameter rotor | US920861 | 1992-07-28 | US5299912A | 1994-04-05 | Evan A. Fradenburgh; Gordon G. Miller |
| A drive system for varying the diameter of a variable diameter rotor has a gear drive system associated with a single coaxial shaft lower end which includes a gear set for increasing or decreasing the speed of rotation of the coaxial shaft relative to the rotor drive shaft to change the length of two or more variable length blades. Utilizing a single shaft system allows a variable diameter rotor drive system to be adapted to gimballed rotors which require shaft flexibility. Since only a single shaft extends through the rotor drive shaft, hub complexity is reduced. | ||||||
| 32 | Locking control and overtravel safety stop system for variable length rotor blades | US700527 | 1976-06-28 | US4080097A | 1978-03-21 | Lee N. Hager; Evan A. Fradenburgh; Jay M. Yarm |
| A locking control system and an overtravel safety top system are presented for a variable length rotor blade system. The lock system has linkage and pawl apparatus operated by a pilot actuated lock shaft to lock and unlock the blade adjustment system. A traveling nut on the lock shaft actuates the lock linkage, either directly or through the lock shaft to lock the blade adjustment system to prevent overretraction or overextension in the event of malfunction of the extension control system. | ||||||
| 33 | Rotor diameter indicator | US628873 | 1975-11-05 | US4007997A | 1977-02-15 | Jay Martin Yarm |
| A variable length blade in telescopic form adapted to be used with similar blades to form a variable diameter rotor or propeller wherein the outer blade portion, at the will of the pilot, is caused to telescope with respect to the inner blade portion by jackscrew action and means are provided for limiting the extending and retracting movements of the blades and also for providing a continuing visual indication of the diameter of the rotor. | ||||||
| 34 | Variable diameter propellers | US3501248D | 1968-05-14 | US3501248A | 1970-03-17 | BROCKER FRIEDRICH W |
| 35 | Airplane propeller | US48053043 | 1943-03-25 | US2428225A | 1947-09-30 | JOHNSTON ROBERT M |
| 36 | Flexible, variable-diameter propeller | US45742942 | 1942-09-05 | US2425353A | 1947-08-12 | SPITZER JR LYMAN |
| 37 | Screw-propeller | US26476118 | 1918-11-29 | US1365132A | 1921-01-11 | ABINGTON VESSEY ERNEST |
| 38 | Churn | US268969D | US268969A | 1882-12-12 | ||
| 39 | Churn-dasher | US266011D | US266011A | 1882-10-17 | ||
| 40 | Improvement in dining-tables | US116419D | US116419A | 1871-06-27 | ||
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