An analytical analysis of the dynamical behavior of the tuned-mass vibration absorber is presented, and the notion of optimum damping is introduced. Computational techniques for calculating optimum damping coefficients are developed and three representative numerical examples are solved. A nonlinear servo-control system is designed to achieve inflight automatic tuning of the tuned-mass absorber in the face of varying helicopter rotor speeds. The practical aspects of implementing active vibration absorbers are studied and some specific circuits and hardware schemes are proposed. A spring-linkage (parallelogram) mount, a cantilever-wing tuned-mass absorber, and an active absorber are designed for implementation and testing on a full scale mock-up of a Cobra helicopter wing. (Modified author abstract)
Vibration Absorbers for Rocket Launchers Mounted on Helicopters: Analytical Analysis and Implementation Techniques
1974
87 pages
Report
No indication
English
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