-
公开(公告)号:US12006027B2
公开(公告)日:2024-06-11
申请号:US18172370
申请日:2023-02-22
发明人: Amey Damjee
IPC分类号: B64C27/51 , B64C27/00 , B64U30/20 , B64U30/297
CPC分类号: B64C27/51 , B64C27/001 , B64U30/20 , B64U30/297 , B64C2027/003
摘要: An improved propeller system is disclosed, including at least one resilient component configured with a mounting arrangement of a propeller of the propeller system. The resilient component is made of a resilient material that allows the propeller to tilt about a tethering axis under conditions of differential lift force on blades of the propeller under an advancing condition and a retreating condition. The resilient component includes a pair of cutouts for locating inserts made of a rigid material and positioned with a longitudinal axis of the inserts oriented in radial direction. The orientation of the inserts results in a radially oriented line contact between the propeller and the inserts to ensure that tilting of the propeller is about longitudinal axis of the inserts, defining the tethering axis of the propeller system.
-
公开(公告)号:US11834166B2
公开(公告)日:2023-12-05
申请号:US16758135
申请日:2018-10-25
发明人: Ankit Mehta
CPC分类号: B64C27/51 , F01D5/16 , F16F15/36 , G01M1/32 , F05D2240/30 , F05D2260/96
摘要: A device for self-balancing a rotating part, such as a propeller, along a given axis is disclosed. The propeller 102 coupled to, a drive shaft with freedom for linear movement along longitudinal axis L-L; at least one pair of levers 614/616, comprising a first lever 614-1/616-1 and a second lever 614-2/616-2, that are pivotally mounted on mounting plate 606 at two diametrically opposite points 618; and at least one pair of weights 622 fixed at external ends of the levers 614/616. inner ends of levers 614/616 are operatively coupled to the propeller 102 such that when propeller 102 undergoes a linear movement in any direction along the longitudinal, axis L-L due to unbalance, inner ends of levers are, moved to cause the weights 622 to move to provide a balancing force to neutralize the unbalance in the propeller. An embodiment with only one pair of levers is also disclosed.
-
3.
公开(公告)号:US11697492B2
公开(公告)日:2023-07-11
申请号:US17225763
申请日:2021-04-08
发明人: Mark Alger , Randall Kohuth , Dean Campbell
IPC分类号: B64C27/51
CPC分类号: B64C27/51
摘要: A piston assembly for a lead-lag damper for a blade mounted on a rotor of a helicopter includes a piston-rod that has an inside surface and a piston-head that extends radially outward therefrom. The piston-rod has two ports extending therethrough on opposing sides of the piston-head. A sleeve is positioned in the piston-rod and has two annular passages that communicate with the respective ports. A valve spool is disposed in and slidingly engages the sleeve. The valve spool has a channel which is in variable fluid communication with two passages. The piston assembly includes a biasing member that biases the valve spool axially away from it. The channel has an axial width configured to variably regulate fluid flow between the two ports to control dampening of the piston-rod in response to centrifugal forces applied to the valve spool.
-
公开(公告)号:US20190002085A1
公开(公告)日:2019-01-03
申请号:US15636448
申请日:2017-06-28
IPC分类号: B64C11/06 , B64C29/00 , B64C11/32 , F16F15/121
CPC分类号: B64C11/06 , B64C11/32 , B64C27/35 , B64C27/51 , B64C27/635 , B64C29/0033 , F16C23/043 , F16C27/02 , F16C2326/43 , F16F15/1208 , F16F15/121 , F16F15/124
摘要: A proprotor system operable for use on a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode. The proprotor system includes a rotor hub and a plurality of proprotor blades coupled to the rotor hub such that each proprotor blade has three independent degrees of freedom relative to the rotor hub including blade pitch about a pitch change axis, blade flap about a flapping axis and lead-lag about a lead-lag axis. Each of a plurality of spherical bearings couples one of the proprotor blades with the rotor hub. In addition, each of a plurality of lead-lag dampers couples one of the proprotor blades with the rotor hub, wherein each lead-lag damper is aligned with the pitch change axis of the respective proprotor blade, thereby providing pitch independent lead-lag damping.
-
公开(公告)号:US20180229836A1
公开(公告)日:2018-08-16
申请号:US15516442
申请日:2015-08-03
发明人: Adrial Kirchen , James Orbon
IPC分类号: B64C27/51 , B64C27/635 , B03C1/30
CPC分类号: B64C27/51 , B03C1/30 , B64C27/635
摘要: A blade damper with a magnetic contaminants trap includes, a housing defining a cavity, a piston in operable communication with the housing dividing the cavity into at least a first chamber and a second chamber, a passageway in operable communication with the cavity configured to allow fluid within the cavity to move between the first chamber and the second chamber through the passageway, and at least one magnet in operable communication with fluid in at least one of the cavity and the passageway, such that magnetic contaminants are prevented from freely moving about within the fluid after having been attracted toward the at least one magnet by a magnetic field of the at least one magnet.
-
公开(公告)号:US09982737B2
公开(公告)日:2018-05-29
申请号:US15085030
申请日:2016-03-30
申请人: Hutchinson
发明人: Eduardo Beltran , Florian Briche
CPC分类号: F16F7/087 , B64C27/51 , B64F5/60 , F16F1/38 , F16F7/09 , F16F2222/04 , F16F2224/025 , F16F2230/0047 , F16F2230/24 , F16F2236/103
摘要: A device configured for insertion between two parts of a rotary wing aircraft that are likely to undergo a repeated relative movement. The device includes at least two frame elements intended to be mounted on at least one of the two parts of the aircraft, and at least one layer of elastomer positioned between the two frame elements, the at least one layer defined by a first surface belonging to the inner volume of the device, a second surface also belonging to the inner volume of the device, and an outer surface not belonging to the inner volume of the device. The inner volume of the device includes at least two independent pouches each positioned at a predetermined distance from the outer surface, each pouch being filled with a product capable of flowing outside its pouch when a crack has spread from said outer surface toward the pouch in question.
-
公开(公告)号:US09879753B2
公开(公告)日:2018-01-30
申请号:US14772017
申请日:2014-03-13
IPC分类号: F16F15/16 , B64C27/39 , F16F1/48 , F16F9/14 , B64C27/51 , B64C27/635 , B23P15/00 , F16F9/12 , F16F9/36
CPC分类号: F16F15/165 , B23P15/00 , B23P2700/01 , B64C27/39 , B64C27/51 , B64C27/635 , F16F1/48 , F16F9/12 , F16F9/145 , F16F9/369
摘要: Rotary dampers and systems for use and installation within a rotary winged aircraft, and related methods, are provided herein. In some aspects, a rotary damper includes a housing having a rotor assembly positioned inside the housing. The rotary damper may further include at least one resilient member disposed adjacent to an outer portion of the housing. The at least one resilient member is externally visible from outside of the rotary damper. In some aspects, the resilient member includes a torsional spring of the rotary damper. In certain aspects, the resilient member is disk shaped and slidable within a portion of the rotary damper. In some aspects, at least one primary liquid orifice is provided in a portion of the at least one rotor member. In some aspects, at least one pressure equalization port is disposed within a portion of the rotor assembly.
-
公开(公告)号:US20170283047A1
公开(公告)日:2017-10-05
申请号:US15508346
申请日:2015-09-29
发明人: Steven D. Weiner , William J. Eadie
CPC分类号: F16F15/02 , B64C1/0009 , B64C7/00 , B64C13/04 , B64C13/18 , B64C13/50 , B64C13/503 , B64C19/00 , B64C27/001 , B64C27/006 , B64C27/008 , B64C27/08 , B64C27/10 , B64C27/12 , B64C27/14 , B64C27/16 , B64C27/32 , B64C27/322 , B64C27/33 , B64C27/467 , B64C27/473 , B64C27/48 , B64C27/51 , B64C27/52 , B64C27/54 , B64C27/57 , B64C27/78 , B64C27/80 , B64C27/82 , B64C2027/004 , B64C2027/8209 , B64C2027/8227 , B64C2027/8236 , B64C2027/8263 , B64C2027/8272 , B64C2027/8281 , B64C2201/024 , B64D35/06 , B64D39/00 , B64D39/06 , B64D45/02 , F02C9/28 , F05D2220/329 , F05D2270/021 , F16D13/52 , F16D13/72 , F16D13/74 , F16H37/02 , G05D1/0077 , G05D1/0202 , G05D1/0204 , G05D1/08 , G05D1/0816 , G05D1/0858 , G06F19/00
摘要: 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.
-
公开(公告)号:US09656744B2
公开(公告)日:2017-05-23
申请号:US14283515
申请日:2014-05-21
IPC分类号: B64C27/635 , B64C27/58 , B64C27/59 , B64C27/54 , B64C27/51 , F16C11/06 , F16C11/04 , F16C23/02
CPC分类号: B64C27/54 , B64C27/51 , B64C27/58 , B64C27/59 , B64C27/635 , F16C11/045 , F16C11/0614 , F16C11/0695 , F16C23/02 , F16C2326/43
摘要: An aircraft includes a rotor blade and a rotor hub system. The rotor hub system includes a lead-lag damper having a rod end and being operably associated with the rotor blade; a blade adapter having a first arm and an opposing second arm; a pin carried by the blade adapter and configured to secure in position via the first arm and the second arm; and an actuator secured to the pin and configured to adjust the position of the lead-lag rod end relative to the first arm and the second arm.
-
公开(公告)号:US09637228B2
公开(公告)日:2017-05-02
申请号:US14682338
申请日:2015-04-09
申请人: AIRBUS HELICOPTERS
发明人: Stephane Mazet , Sandra Bencardino
CPC分类号: B64C27/54 , B64C27/322 , B64C27/51
摘要: A rotor having a hub and a plurality of lift assemblies, the rotor having one lead/lag abutment mechanism per lift assembly. Each abutment mechanism includes an elastomer spacer strip and two C-shaped metal clips engaged respectively on a first base and on a second base of the strip. Two fastener pins each pass through a clip and the longitudinal projections of a base and through an orifice in the hub.
-
-
-
-
-
-
-
-
-