GB1120193A - Vibration absorbing device - Google Patents
Vibration absorbing deviceInfo
- Publication number
- GB1120193A GB1120193A GB4331765A GB4331765A GB1120193A GB 1120193 A GB1120193 A GB 1120193A GB 4331765 A GB4331765 A GB 4331765A GB 4331765 A GB4331765 A GB 4331765A GB 1120193 A GB1120193 A GB 1120193A
- Authority
- GB
- United Kingdom
- Prior art keywords
- members
- shaft
- hub
- housing
- rotatably mounted
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/001—Vibration damping devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/22—Compensation of inertia forces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/001—Vibration damping devices
- B64C2027/003—Vibration damping devices mounted on rotor hub, e.g. a rotary force generator
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Combined Devices Of Dampers And Springs (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
1,120,193. Reducing vibrations on helicopters. BOEING CO. 12 Oct., 1965 [31 Dec., 1964 (2)], No. 43317/65. Headings B7G and B7W. [Also in Division F2] In a vibration absorbing device for a set of rotor blades of a helicopter annular housings 25, 22, rotatably mounted on a shaft 21 attached to a rotor head hub (18), Fig. 2 (not shown), and accommodated in a housing 28 secured to the fuselage of the helicopter by a member 29, pairs of cylindrical inertia members (50, 51), Fig. 6 (not shown), and (53, 54), Fig. 7 (not shown), are movably housed within the annular chambers (49), (52) respectively of the housings 22, 25 which, by means of planet and ring gearing 32, 36 and 42, 40 respectively are rotated in opposite directions at three times the speed of the rotor hub 18, i.e. the product of the speed of the hub 18 and the number of rotor blades. The annular chambers (49, 52) may be partially filled with a liquid. In a modification, Fig. 8 (not shown), a housing (56) carried by the hub (18) is rotatably mounted at (60, 61) to a stationary member (58) connected to the fuselage by a member (57) and carries a gear ring (75) which co-operates with gears (72, 83) fast on the outer ends of shafts (70, 81) which are rotatably mounted in sleeves (62, 63) in opposing sides of the member (58). The other end of the shaft (70) is splined at (78) to a housing (80) which rotates at the same speed as the shaft (70) and which has an annular chamber (103) in which at least two cylindrical members, one shown at (104), are disposed. The inner end of the shaft (81) is splined at (85) to a housing (87) which comprises a pair of sections (88, 89) connected by nuts (93) and bolts (92) and having annular chambers (99, 101) respectively, each of which receives at least two cylindrical weights such as (100), or (102). The housing (87) is rotatably mounted on bearings (94, 98) supported upon the sleeves (63, 62) and on bearings (95, 97) supported upon annular projections (96, 79) of the housing (80). Since the housings (80, 87) rotate in opposite directions the vibration damper synthesizes an elliptical locus, which is produced in the vertical-longitudinal plane at the hub (18) by the vibrations created by the rotor blades (15, 16, 17), Fig. 1 (not shown). Any of the annular chambers can be partially filled with liquid. In both of the embodiments described, the housings 22, 25 and (80, 87), instead of being driven by gearing arrangements, could be driven, e.g. synchronous motors connected to each of the housings and driven by a generator connected to the hub 18. A single housing with at least two weights movable therein in an annular chamber could be used to balance out certain periodic vibrations. In a further modification, Figs. 9-11 (not shown), arcuate members (122, 125), of the same weight, are rotatably mounted about a shaft (121) connected to a driving hub (118) and another pair of arcuate members (128, 132) of the same weight, but different from that of the members (122, 125), are rotatably mounted about the hubs (129, 133) of the members (122, 125) respectively. The members (122, 125, 128, 132) are driven at three times the speed of a drive shaft (121) by planet, sun, and ring gearing the members (122, 125) being rotated in the same direction as, and the members (128, 132) in the opposite direction to, the shaft (121). The members (122, 125, 128, 132), the shaft (121) and their gearing are enclosed within a housing (136) which is secured to the fuselage by means of a member (137). The outer ring gears (157, 169, 198, 210) of the four sets of gearings mesh respectively with servomotors (158, 170, 204, 211) which are normally not energized, however, they can be energized so that the positions of the weights (122, 125) and (128, 132) can be moved in relation to the others so that the resultant centrifugal forces of the pairs of members (122, 125) and (128, 132) can be varied and their phases can be regulated to oppose and balance out the forcing longitudinal and lateral vibratory components at the hub. In a circuit for energizing the servomotors (170, 211), the output of an accelerometer (138) mounted on top of the shaft (137) for sensing longitudinal vibrations, is connected to a band-pass filter and phase control (221) which is connected to a pair of phase detectors (222, 223), Fig. 12 (not shown), each of which receives the output of a bi-stable oscillator (224, 225) having inputs from diametrically opposed magnetic pick-offs (226, 227) and (229, 230) on arcuate members (128, 132 respectively which have magnetic inserts (228, 231). The outputs of the phase detectors 222, 223 are connected, through filters and power amplifiers (232, 233) to the servomotors (170, 211). An accelerometer 139 and a similar circuit, Fig. 13 (not shown), controls the servomotors (158, 204).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US422830A US3219120A (en) | 1964-12-31 | 1964-12-31 | Vibration absorbing system |
US422741A US3298443A (en) | 1964-12-31 | 1964-12-31 | Vibration absorbing system |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1120193A true GB1120193A (en) | 1968-07-17 |
Family
ID=27025732
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB4331765A Expired GB1120193A (en) | 1964-12-31 | 1965-10-12 | Vibration absorbing device |
Country Status (3)
Country | Link |
---|---|
DE (1) | DE1456013A1 (en) |
FR (1) | FR1473921A (en) |
GB (1) | GB1120193A (en) |
Cited By (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2006135405A3 (en) * | 2004-08-30 | 2007-02-22 | Lord Corp | Helicopter vibration control system and rotary force generator for canceling vibrations |
WO2009126626A3 (en) * | 2008-04-07 | 2009-12-10 | Lord Corporation | Helicopter hub mounted vibration control and circular force generation systems for canceling vibrations |
EP2150460A1 (en) * | 2007-04-24 | 2010-02-10 | Bell Helicopter Textron Inc. | Rotor hub vibration attenuator |
US7722322B2 (en) | 2004-08-30 | 2010-05-25 | Lord Corporation | Computer system and program product for controlling vibrations |
WO2010068942A1 (en) | 2008-12-12 | 2010-06-17 | Lord Corporation | Helicopter vibration control system and rotating assembly rotary forces generators for canceling vibrations |
US8090482B2 (en) | 2007-10-25 | 2012-01-03 | Lord Corporation | Distributed active vibration control systems and rotary wing aircraft with suppressed vibrations |
US8267652B2 (en) | 2004-08-30 | 2012-09-18 | Lord Corporation | Helicopter hub mounted vibration control and circular force generation systems for canceling vibrations |
US8435002B2 (en) | 2004-08-30 | 2013-05-07 | Lord Corporation | Helicopter vibration control system and rotating assembly rotary forces generators for canceling vibrations |
US8474745B2 (en) | 2007-04-24 | 2013-07-02 | Textron Innovations Inc. | Rotor hub vibration attenuator |
US9452828B2 (en) | 2007-04-24 | 2016-09-27 | Textron Innovations Inc. | Rotor hub vibration attenuator |
EP3209558A4 (en) * | 2014-10-21 | 2018-05-16 | Sikorsky Aircraft Corporation | Vibration control assembly for an aircraft and method of controlling aircraft vibration |
US10065730B2 (en) | 2014-01-22 | 2018-09-04 | Bell Helicopter Textron Inc. | Active vibration control system with non-concentric revolving masses |
EP3421358A1 (en) * | 2017-06-30 | 2019-01-02 | LEONARDO S.p.A. | Rotor for a hover-capable aircraft |
US10308354B2 (en) | 2011-02-04 | 2019-06-04 | Lord Corporation | Rotary wing aircraft vibration control system with resonant inertial actuators |
US10526076B2 (en) | 2007-04-24 | 2020-01-07 | Textron Innovations Inc. | Rotor hub vibration attenuator |
EP3766778A1 (en) | 2019-07-19 | 2021-01-20 | LEONARDO S.p.A. | Rotor for a hover-capable aircraft |
EP3766779A1 (en) | 2019-07-19 | 2021-01-20 | LEONARDO S.p.A. | Rotor for a hover-capable aircraft |
CN112407252A (en) * | 2020-10-30 | 2021-02-26 | 中国直升机设计研究所 | Helicopter embedded type accurate balance weight system and weight method |
CN114524096A (en) * | 2022-03-10 | 2022-05-24 | 广州一诺智能信息工程有限公司 | Automatic obstacle-avoiding surveying and mapping unmanned aerial vehicle for water conservancy |
CN117543887A (en) * | 2023-12-25 | 2024-02-09 | 广东智赢半导体技术有限公司 | Vibration-proof servo motor |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2768995B1 (en) * | 1997-10-01 | 1999-12-03 | Eurocopter France | PENDULUM ROTOR HEAD RESONATOR |
-
1965
- 1965-10-12 GB GB4331765A patent/GB1120193A/en not_active Expired
- 1965-11-30 FR FR40316A patent/FR1473921A/en not_active Expired
- 1965-12-29 DE DE19651456013 patent/DE1456013A1/en active Pending
Cited By (54)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8162606B2 (en) | 2004-08-30 | 2012-04-24 | Lord Corporation | Helicopter hub mounted vibration control and circular force generation systems for canceling vibrations |
US9073627B2 (en) | 2004-08-30 | 2015-07-07 | Lord Corporation | Helicopter vibration control system and circular force generation systems for canceling vibrations |
US8267652B2 (en) | 2004-08-30 | 2012-09-18 | Lord Corporation | Helicopter hub mounted vibration control and circular force generation systems for canceling vibrations |
US8480364B2 (en) | 2004-08-30 | 2013-07-09 | Lord Corporation | Computer system and program product for controlling vibrations |
US7722322B2 (en) | 2004-08-30 | 2010-05-25 | Lord Corporation | Computer system and program product for controlling vibrations |
US10392102B2 (en) | 2004-08-30 | 2019-08-27 | Lord Corporation | Helicopter vibration control system and circular force generation systems for canceling vibrations |
US7942633B2 (en) | 2004-08-30 | 2011-05-17 | Lord Corporation | Helicopter vibration control system and rotary force generator for canceling vibrations |
WO2006135405A3 (en) * | 2004-08-30 | 2007-02-22 | Lord Corp | Helicopter vibration control system and rotary force generator for canceling vibrations |
US8435002B2 (en) | 2004-08-30 | 2013-05-07 | Lord Corporation | Helicopter vibration control system and rotating assembly rotary forces generators for canceling vibrations |
US7448854B2 (en) | 2004-08-30 | 2008-11-11 | Lord Corporation | Helicopter vibration control system and rotary force generator for canceling vibrations |
US8313296B2 (en) | 2004-08-30 | 2012-11-20 | Lord Corporation | Helicopter vibration control system and rotary force generator for canceling vibrations |
US9776712B2 (en) | 2005-08-30 | 2017-10-03 | Lord Corporation | Helicopter vibration control system and circular force generation systems for canceling vibrations |
EP2150460A4 (en) * | 2007-04-24 | 2013-02-27 | Bell Helicopter Textron Inc | Rotor hub vibration attenuator |
US8424799B2 (en) | 2007-04-24 | 2013-04-23 | Textron Innovations Inc. | Rotor hub vibration attenuator |
US10526076B2 (en) | 2007-04-24 | 2020-01-07 | Textron Innovations Inc. | Rotor hub vibration attenuator |
US8474745B2 (en) | 2007-04-24 | 2013-07-02 | Textron Innovations Inc. | Rotor hub vibration attenuator |
EP2150460A1 (en) * | 2007-04-24 | 2010-02-10 | Bell Helicopter Textron Inc. | Rotor hub vibration attenuator |
US9452828B2 (en) | 2007-04-24 | 2016-09-27 | Textron Innovations Inc. | Rotor hub vibration attenuator |
US9139296B2 (en) | 2007-04-24 | 2015-09-22 | Textron Innovations Inc. | Rotor hub vibration attenuator |
US8639399B2 (en) | 2007-10-25 | 2014-01-28 | Lord Corporaiton | Distributed active vibration control systems and rotary wing aircraft with suppressed vibrations |
US8090482B2 (en) | 2007-10-25 | 2012-01-03 | Lord Corporation | Distributed active vibration control systems and rotary wing aircraft with suppressed vibrations |
CN102056798B (en) * | 2008-04-07 | 2014-05-28 | 洛德公司 | Helicopter hub mounted vibration control and circular force generation systems for canceling vibrations |
WO2009126626A3 (en) * | 2008-04-07 | 2009-12-10 | Lord Corporation | Helicopter hub mounted vibration control and circular force generation systems for canceling vibrations |
WO2010068942A1 (en) | 2008-12-12 | 2010-06-17 | Lord Corporation | Helicopter vibration control system and rotating assembly rotary forces generators for canceling vibrations |
US10308354B2 (en) | 2011-02-04 | 2019-06-04 | Lord Corporation | Rotary wing aircraft vibration control system with resonant inertial actuators |
US10543911B2 (en) | 2011-02-04 | 2020-01-28 | Lord Corporation | Rotary wing aircraft vibration control system with resonant inertial actuators |
US10814963B2 (en) | 2014-01-22 | 2020-10-27 | Bell Helicopter Textron Inc. | Active vibration control system with non-concentric revolving masses |
US10065730B2 (en) | 2014-01-22 | 2018-09-04 | Bell Helicopter Textron Inc. | Active vibration control system with non-concentric revolving masses |
US11884385B2 (en) | 2014-01-22 | 2024-01-30 | Textron Innovations Inc. | Active vibration control system with non-concentric revolving masses |
EP3209558A4 (en) * | 2014-10-21 | 2018-05-16 | Sikorsky Aircraft Corporation | Vibration control assembly for an aircraft and method of controlling aircraft vibration |
US11235868B2 (en) | 2014-10-21 | 2022-02-01 | Sikorsky Aircraft Corporation | Vibration control assembly for an aircraft and method of controlling aircraft vibration |
US10906636B2 (en) | 2014-10-21 | 2021-02-02 | Sikorsky Aircraft Corporation | Vibration control assembly for an aircraft and method of controlling aircraft vibration |
EP3421359A1 (en) | 2017-06-30 | 2019-01-02 | LEONARDO S.p.A. | Rotor for a hover-capable aircraft |
WO2019002513A1 (en) | 2017-06-30 | 2019-01-03 | Leonardo S.P.A. | Rotor for a hover-capable aircraft |
KR20200036817A (en) * | 2017-06-30 | 2020-04-07 | 레오나르도 에스피에이 | Hoverable aircraft rotor |
EP3421358A1 (en) * | 2017-06-30 | 2019-01-02 | LEONARDO S.p.A. | Rotor for a hover-capable aircraft |
KR102553860B1 (en) | 2017-06-30 | 2023-07-10 | 레오나르도 에스.피.에이. | Rotors for hoverable aircraft |
US11319061B2 (en) | 2017-06-30 | 2022-05-03 | Leonardo S.P.A. | Rotor for a hover-capable aircraft |
JP2020525346A (en) * | 2017-06-30 | 2020-08-27 | レオナルド・エッセ・ピ・ア | Rotor for airborne stationary aircraft |
CN110753661A (en) * | 2017-06-30 | 2020-02-04 | 列奥纳多股份公司 | Rotor for an aircraft capable of hovering |
JP7053686B2 (en) | 2017-06-30 | 2022-04-12 | レオナルド・エッセ・ピ・ア | Rotor for aerial stationary aircraft |
RU2757548C2 (en) * | 2017-06-30 | 2021-10-18 | ЛЕОНАРДО С.п.А. | Rotor for hover-capable aircraft |
WO2021014234A1 (en) | 2019-07-19 | 2021-01-28 | Leonardo S.P.A. | Rotor for a hover-capable aircraft |
WO2021014235A1 (en) | 2019-07-19 | 2021-01-28 | Leonardo S.P.A. | Rotor for a hover-capable aircraft |
EP3766779A1 (en) | 2019-07-19 | 2021-01-20 | LEONARDO S.p.A. | Rotor for a hover-capable aircraft |
US11738859B2 (en) | 2019-07-19 | 2023-08-29 | Leonardo S.P.A. | Rotor for a hover-capable aircraft |
US11760468B2 (en) | 2019-07-19 | 2023-09-19 | Leonardo S.P.A. | Rotor for a hover-capable aircraft |
EP4269238A2 (en) | 2019-07-19 | 2023-11-01 | Leonardo S.p.a. | Rotor for a hover-capable aircraft |
EP4269238A3 (en) * | 2019-07-19 | 2023-12-27 | Leonardo S.p.a. | Rotor for a hover-capable aircraft |
EP3766778A1 (en) | 2019-07-19 | 2021-01-20 | LEONARDO S.p.A. | Rotor for a hover-capable aircraft |
CN112407252A (en) * | 2020-10-30 | 2021-02-26 | 中国直升机设计研究所 | Helicopter embedded type accurate balance weight system and weight method |
CN114524096A (en) * | 2022-03-10 | 2022-05-24 | 广州一诺智能信息工程有限公司 | Automatic obstacle-avoiding surveying and mapping unmanned aerial vehicle for water conservancy |
CN114524096B (en) * | 2022-03-10 | 2023-07-18 | 广州一诺智能信息工程有限公司 | Water conservancy is with automatic obstacle avoidance survey and drawing unmanned aerial vehicle |
CN117543887A (en) * | 2023-12-25 | 2024-02-09 | 广东智赢半导体技术有限公司 | Vibration-proof servo motor |
Also Published As
Publication number | Publication date |
---|---|
FR1473921A (en) | 1967-03-24 |
DE1456013A1 (en) | 1969-05-29 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
GB1120193A (en) | Vibration absorbing device | |
CA1335239C (en) | Gyrostat propulsion system | |
US3219120A (en) | Vibration absorbing system | |
EP3209558B1 (en) | Vibration control assembly for an aircraft and method of controlling aircraft vibration | |
KR102553860B1 (en) | Rotors for hoverable aircraft | |
JPH0754928A (en) | Opposing method to vibrational propagation of rotational rotor having dynamic unbalance and revolving-torque vector and generator of vibrational couple | |
US7347799B2 (en) | Antivibration device having rotary flyweights and an epicyclic geartrain | |
US3526795A (en) | Torque reaction attitude control device | |
GB1231663A (en) | ||
US20200191237A1 (en) | Variable rotary mass vibration suppression system | |
US3298443A (en) | Vibration absorbing system | |
US2491260A (en) | Pitch control mechanism for helicopters | |
US2211076A (en) | Means for imparting impulses to a system | |
US2371984A (en) | Means for imposing harmonic torques on shafting | |
US2595195A (en) | Governor for helicopter rotor blades | |
GB836957A (en) | Vibratory force producing apparatus | |
US4072066A (en) | Centrifugal force controlled transmission | |
GB2231127A (en) | Thrust apparatus | |
JPS59577A (en) | Inertia propelled engine and inertia motor | |
GB2225424A (en) | Gyroscopic apparatus | |
EP3766779B1 (en) | Rotor for a hover-capable aircraft | |
GB922071A (en) | Improvements in or relating to exciter units for vibratory members | |
SE324493B (en) | ||
SU757209A1 (en) | Unbalance vibration exciter | |
US3363472A (en) | Constant-angular-momentum gyroscope |