A rotorcraft small perturbation linear model is described. Rotor flap, inplane and feathering degrees of freedom, as well as control and augmentation systems are defined in addition to the classical vehicle six degrees of freedom. The primary application was intended to be an analytic tool to assess the handling qualities of a dynamically combined main rotor and body. The modeling method retained the higher frequency response properties which aided in evaluating control and stability augmentation systems.
Rotorcraft Linear Simulation Model. Volume 1: Engineering Documentation
1978
185 pages
Report
No indication
English