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公开(公告)号：KR820000274B1
公开(公告)日：1982-03-15
申请号：KR770003018
申请日：1977-12-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KENIGSBERG IRWIN J , EASTMAN LARRY B
IPC: B64C27/00
Abstract: The rotor(16) & the transmission(14) of a helicopter are mounted on the fuselage(12) by a vibration isolating assembly. The assembly includes a number of elastomeric counts(20,22) each of which incorporates alternate layers of elastomer and metal laminates. The mounts are subject to compression & are located about the axis of the rotor. Four mounts are used, the axes of the forward two intersecting on the roll axis, & the axes of the rearward two also intersecting on the roll axis but further back.
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公开(公告)号：KR820000273B1
公开(公告)日：1982-03-15
申请号：KR770003019
申请日：1977-12-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： NIEBANCK CHARLES F , KLUSMAN STEVEN A , KENIGSBERG IRWIN J
IPC: B64C25/60
Abstract: The aircraft landing gear is suitable for a helicopter (10) and includes a pair of wheels(36, 38) on opposite sides of the aircraft linked by a transvers rod. The wheels are suspended by oleo struts(20,22) which, when the aircraft lands symmetrically, provide desired vertical stiffness and damping characteristics. When the aircraft lands symmetrically, the rod is operated by which-ever wheel 1st touches the ground, and couples the suspensions of the two wheels. The roll mode stiffness is soft enough to avoid ground resonance instability.
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公开(公告)号：FR2332176A1
公开(公告)日：1977-06-17
申请号：FR7629522
申请日：1976-10-01
Applicant: UNITED TECHNOLOGIES CORP , UNITED TECHNOLOGIES CORP
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公开(公告)号：CA1062226A
公开(公告)日：1979-09-11
申请号：CA257611
申请日：1976-07-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KENIGSBERG IRWIN J , PAUL WILLIAM F
Abstract: A helicopter has a plurality of bifilar absorbers mounted on arms radially extended from the hub of the rotor. A bifilar mass of the required weight mounted at the end of an arm of required length to absorb input excitations at a pendulum amplitude of approximately 30.degree. at design forward speed is mounted on an arm twice the length without a reduction in weight of the bifilar mass to limit pendulum amplitude to 15.degree. while maintaining the original force output. Bifilar motion in the linear range with associated elimination of overtuning produces improved bifilar operation at all flight speeds and eliminates second order vibration due to dissimilar motions resulting from overtuning.
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公开(公告)号：CA1066683A
公开(公告)日：1979-11-20
申请号：CA292588
申请日：1977-12-07
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KENIGSBERG IRWIN J , EASTMAN LARRY B
Abstract: HELICOPTER ROTOR AND TRANSMISSION MOUNTING AND VIBRATION ISOLATION SYSTEM A helicopter rotor and transmission mounting and vibration isolation system in which the transmission is supported from the fuselage by a plurality of elastomeric mounts which are selectively positioned and focused to establish a system roll axis and a system pitch axis on opposite sides of the elastomeric mounts and which mount members are of selected stiffness to establish selected roll stiffness and selected pitch stiffness of the system, to establish the natural frequencies of the system sufficiently below the blade passage frequency to minimize the response of the fuselage to forces and moments imparted by the helicopter rotor and to provide selected torque restraint and lift restraint for the system.
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Patent Agency Ranking
公开(公告)号：CA1064455A
公开(公告)日：1979-10-16
申请号：CA258310
申请日：1976-08-03
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KENIGSBERG IRWIN J , CARTER EDWARD S
Abstract: A multibladed helicopter rotor carries at least three bifilar absorbers which are tuned to eliminate in-plane vibrations of the rotor that otherwise would be transmitted to the helicopter fuselage. By drooping the radial support arms for the absorbers out of the plane normal to their axis of rotation, the resultant of the centrifugal forces acting on the pendulous elements of the absorbers and the weight of these elements acts normal to the axes of the tuning pins of the absorbers which minimizes internal frictional damping in the absorbers.
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公开(公告)号：CA1037451A
公开(公告)日：1978-08-29
申请号：CA243594
申请日：1976-01-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： EASTMAN LARRY B , KENIGSBERG IRWIN J
Abstract: SPHERICAL BIFILAR TUNING PIN BUSHING A multibladed helicopter rotor carries at least three bifilar absorbers which are tuned to eliminate in-plane vibrations of the rotor which otherwise would be transmitted to the helicopter fuselage. Improved tuning pin assemblies and cooperating tracking inserts for the absorber reduce the undesirable frictional damping heretofore encountered in bifilar absorbers by centering the pendulous elements of the absorbers relative to their support members and reacting forces normal to centrifugal force by permitting flapping movement of the bifilar mass in the vertical plane.
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公开(公告)号：CA1077454A
公开(公告)日：1980-05-13
申请号：CA292295
申请日：1977-12-02
Applicant: UNITED TECHNOLOGIES CORP
Inventor： NIEBANCK CHARLES F , KLUSMAN STEVEN A , KENIGSBERG IRWIN J
Abstract: AIRCRAFT LANDING GEAR A passive aircraft landing gear system in which the spring rate and damping for aircraft rolling motions about a longitudinal axis are independent of the spring rate and damping for aircraft vertical motions, thereby permitting the landing gear system to optimally accomplish both landing impact attenuation and ground resonance instability abatement.
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公开(公告)号：PL202794A1
公开(公告)日：1978-07-31
申请号：PL20279477
申请日：1977-12-02
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KENIGSBERG IRWIN J , EASTMAN LARRY B
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公开(公告)号：PL202598A1
公开(公告)日：1978-07-31
申请号：PL20259877
申请日：1977-12-02
Applicant: UNITED TECHNOLOGIES CORP
Inventor： NIEBANCK CHARLES F , KLUSMAN STEVEN A , KENIGSBERG IRWIN J
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