Weight reduction is an eternal topic in the history of aircraft development.Based on the weight reduction requirements of an aluminum alloy servo pedestal for a helicopter-borne radar,this paper proposes a lightweight car-bon fiber composite servo pedestal with the same structure.Finite element models of the pedestals made of both ma-terials are established,and a comparison of the static and dynamic characteristics of the two pedestals is conducted.Finally,ply optimization is carried out for the composite material pedestal to further reduce the pedestal mass.The composite material pedestal proposed in this paper meets the operational requirements of the servo system.Compared to the aluminum alloy pedestal,the mass of the proposed pedestal is reduced from 2.86kg to 1.48kg(47.9%reduc-tion),showing a significant weight reduction effect.
carbon fiber compositeservo pedestalfinite element methodply optimization
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