Non-linear simulation of coupled rotor-fuselage response using symbolically derived equations of motion. Part 2: Confirmation and illustrative cases

Abstract

This paper presents a unique simulation method for the ground and air resonance of helicopter rotor systems; the derivation of the full non-linear equations of motion for a rotor-body combination with three rigid blades was discussed in Part 1 of this paper. This section, Part 2, addresses the confirmation of the simulation and includes several unique applications that take advantage of the non-linear capability of the resulting simulation. The symbolic processing software that performed the derivation converted the equations of motion into a high-level language. This code is then incorporated into an interactive numerical methods environment. The modelling method includes all terms, including non-linear and trigonometric functions, and produces inherently highly reliable code results from eliminating manual coding of the equations of motion.