Publication Date:
2019-07-12
Description:
The dynamic response and aeroelastic stability of rotating beams such as helicopter blades is investigated analytically. The Hamilton principle is used to formulate the equations of motion for extensional and inextensional beams with precone angles and variable pitch angles, taking higher-order nonlinearities into account. The derivation of the equations and their approximate solution by a Galerkin procedure are explained in detail, and numerical results of equilibrium solutions and stability analyses are presented graphically.
Keywords:
AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Type:
Vertica (ISSN 0360-5450); 10; 2 19; 151-169
Format:
text
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