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A New Approach to Rotor Blade Dynamic Analysis

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A method, involving the use of an integrating matrix operator, is developed for calculating closed form numerical solutions to linear differential equations.The procedures developed yield the time history of the dependent variables due to any forcing function and initial values by simple matrix multiplication. A closed form steady state solution is further shown for the special case of periodic coefficients and periodic forcing. The method is applied to the equations of motion of a two degree of freedom helicopter rotor blade. Due to the absence of physical restrictions on the coefficients of the equations of motion (except that they may not be functions of the dependent variables), it is seen that the effects of Mach number and reversed flow may be handled in a nearly exact manner when linear conditions exist. The steady state solution to the complete nonlinear equations is treated as a perturbation on a good linear approximation. An iterative scheme is shown for this solution. Illustrative numerical results are given showing the effects of several parameters on stability and the convergence of the nonlinear steady state solutions.
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Document Type: Research Article

Affiliations: Engineering Analysis, Kaman Aircraft Corporation, Bloomfield, Connecticut

Publication date: 1965-07-01

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  • The Journal of the American Helicopter Society is the world's only scientific journal dedicated to vertical flight technology. It is a peer-reviewed technical journal published quarterly by AHS International and presents innovative papers covering the state-of-the-art in all disciplines of rotorcraft design, research and development. (Please note that AHS members receive significant discounts on articles and subscriptions.)

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