Dynamic analysis of a helicopter blade subjected to the aerodynamic loads based on Euler-Bernoulli beam theory

ABSTRACT

In this paper, based on Euler-Bernoulli beam theory, the vibration of a helicopter blade is studied. In this regard, the partial differential equation of motion is obtained and solved for a clamped beam numerically. The aerodynamic forces are introduced in terms of the pilot parameters included the collective pitch, lateral cyclic, longitudinal cyclic, and built-in twist on the blade deformation. Moreover, the effects of the blade rotational angular velocity, flight altitude, the blade length, and induce velocity on the blade deflection are studied. The results show that the blade deformation will be oscillating in terms of time and it is very sensitive to the control parameters, its geometry, and the environmental conditions. Moreover, it is observed that the pilot coefficients have more effect on the blade deformation in comparison with other parameters.

KEYWORDS:

• Blade vibrations
• Euler-Bernoulli beam
• aerodynamic force
• phase diagram
• pilot coefficients

Disclosure statement

No potential conflict of interest was reported by the authors.

Data availability statement

The authors confirm that the data supporting the findings of this study are available within the article [and/or] its supplementary materials.

Additional information

Funding

This research did not receive any specific grant from funding agencies in the public, commercial, or not-for-profit sectors.

Notes on contributors

Hamed Raissi

Hamed Raissi has a Ph.D. in Mechanical Engineering. Currently, He works as a teacher at the Shahid Chamran University of Ahvaz. He has studied the shape memory polymers, composite plates, and FG materials. His favorite fields are impact theory, blast, nonlinear vibration, and stress analysis.