Active vibration control of rotorcraft driveshaft-airframe dynamics

Hans A. DeSmidt, K. W. Wang, Edward Smith

Research output: Contribution to journalConference article

6 Scopus citations

Abstract

The active vibration control of a coupled fuselage-tailrotor drivetrain structure is presented. A finite element method is developed for this type of structure. A baseline study on the model shows that shaft imbalance and aerodynamic loading have a significant effect on hanger bearing loads and flexible coupling misalignments. Additionally, it indicates that by properly accounting for the actuator gap size with the control law, non-contacting magnetic actuators can be used in the control system. For this particular model, a 95% bearing load reduction in forward flight is achieved with two actuators which weigh three pounds and consume three amps of current.

Original languageEnglish (US)
Pages (from-to)472-488
Number of pages17
JournalAnnual Forum Proceedings - American Helicopter Society
Volume1
StatePublished - Jan 1 1998
EventProceedings of the 1998 54th Annual Forum. Part 2 (of 2) - Washington, DC, USA
Duration: May 20 1998May 22 1998

All Science Journal Classification (ASJC) codes

  • Transportation
  • Aerospace Engineering

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