Rotor Dynamics and Helicopter Stability: Development of a Unified Mathematical Theory of the Steady and Disturbed Motion of a Helicopter with Particular Emphasis on the Dynamical Aspects of the Problem

Abstract

The aerodynamic force on an element dx1 of the rotor blade produces a moment about any point, and the component of this moment along the flapping hinge determines the flapping motion of the blade. The air force on an element being i4 dX4‘+Jt d/Y4’+k1 dZ,‘, the moment dG’, say, about the hinge F is given by

Citation

Price, H.L. (1963), "Rotor Dynamics and Helicopter Stability: Development of a Unified Mathematical Theory of the Steady and Disturbed Motion of a Helicopter with Particular Emphasis on the Dynamical Aspects of the Problem", Aircraft Engineering and Aerospace Technology, Vol. 35 No. 7, pp. 195-199. https://doi.org/10.1108/eb033749