Author Type

Graduate Student

Date of Award

1986

Document Type

Thesis

Publication Status

Version of Record

Submission Date

October 2026

Thesis/Dissertation Advisor [Chair]

Goankar, Gopal

Abstract

Flight tests of an open loop higher harmonic vibration control system were conducted on an S-76A helicopter during the early part of 1985. This paper discusses the design, conduct and results of those tests. The flight tests included evaluations of Higher Harmonic Control (HHC) inputs in the longitudinal, lateral and collective axes at varying amplitudes and phases. These flight tests have demonstrated the feasibility of HHC on a medium size, high speed helicopter. Significant vibration reductions throughout the aircraft were demonstrated at forward speeds up to 150 knots. The capability of HHC to reduce vibrations was also demonstrated at varying rotor speeds and during maneuvers. Structural data obtained during testing, showed a general increase in control system loads during HHC operation. However, no loads were above structural limits and it appears that a control system could be designed with sufficient strength to accept all HHC loads.

Extent

58 p.

Comments

College of Engineering and Computer Science|Thesis (M.S.E.)--Florida Atlantic University, 1986.|FAU Electronic Theses and Dissertations Collection|College of Engineering and Computer Science

Identifier

FADT14341

Format

pdf

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