Smart Fuselage Sections for Optimally Distributed Control of Helicopter Airframe Vibrations

摘要

1. Optimally distributed actuation feasibility study 1) A Reduced Order Airframe Model was utilized 2) A hybrid optimization method was formulated to simultaneously determine actuator locations and control effort 3) Optimally distributed actuation configurations were compared to a centralized actuator configuration 4) The optimally distributed actuator configurations are significantly more effective than a centralized actuator configuration. 2. Smart Fuselage Realization 1) Two actuation concepts have been proposed for semi-monocoque airframe structures 2) A Smart Fuselage realization methodology has been formulated, and followed to study a 0.3 scale tailboom model 3) Both the Reduced Order and Finite Element models of the 0.3 scale tailboom are dynamically similar 4) A case study of actuation realization was conducted on the 0.3 scale tailboom models (ROM & FEM) 1 A pair of actuation moments in the Reduced Order Model can be realized as 6 actuation forces in the Finite Element Model 2 The actuation configurations of both tailboom models produce similar control authorities.