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.

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

IPC: B64C27/51 ,  B64C27/00 ,  B64C

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

IPC: B64C27/51 ,  B64C27/00 ,  B64C27/12

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.

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

IPC: B64C27/51 ,  B64C27/00 ,  B64C27/32

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.