Study on Vibratory Loads of Rotor with Trailing Edge Excitation

Shi Ming Liu; Wei Dong Yang; Jie Wu

doi:10.4028/www.scientific.net/AMR.1044-1045.877

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HomeAdvanced Materials ResearchAdvanced Materials Research Vols. 1044-1045Study on Vibratory Loads of Rotor with Trailing...

Study on Vibratory Loads of Rotor with Trailing Edge Excitation

Abstract:

To investigate the vibratory load of rotor with trailing edge excitation, and to study the relationship between TEF motion and hub vibratory load, a comprehensive model is built based on a conventional rotor modeling. Both the inertial force and aerodynamic force of TEF are considered. Effects of frequency, phase and amplitude of the excitation on hub vibration are discussed. The results indicate that with proper phase, hub vibration can be reduced with any of 2-5/rev trailing edge excitation. Within a reasonable range, the change in 4/rev hub vibration is more obvious with larger flap deflection. Control laws of several vibration directions are different, so various directions should be considered overall for optimal vibration control. Light TEFs are beneficial for vibration control.

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Periodical:

Advanced Materials Research (Volumes 1044-1045)

Pages:

877-880

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.1044-1045.877

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Online since:

October 2014

Authors:

Shi Ming Liu*, Wei Dong Yang, Jie Wu

Keywords:

Helicopter, Load, Trailing Edge Flap (TEF), Vibration

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* - Corresponding Author

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