Active Vibration Control of the Lynx Helicopter Airframe (original) (raw)

48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2007

Abstract

Three mathematical models of the same structure, the Lynx airframe, are used in th is generic study together with various types of hub loads to determine optimal actuator configurations for an active vibration control system. One of the mathematical models is a FE model while the two others are based on data from modal analyses of the same airframe but at low and high forcing level. An exhaustive search is used to establish a ranking of the top 100 actuator configurations for each combination of mathematical model and type of hub load excitation. The actuator configurations are compared with regard to locations and predicted reductions. An active vibration control experiment is conducted on the Lynx airframe using the filtered x-LMS algorithm.

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