B.N. Burtsev

The development results of the coaxial-rotor lifting system generalized mathematical model are discussed. The coaxial-rotor system is modeled by means of aeroelastic blade couplings through signal control links and also by aeroelastic blade interaction in coaxial rotor vortex. An unlinear blade vortex model is developed on the basis of lifting surface theory to model this phenomenon. The functional capabilities consist in modeling either stationary or unstationary modes of flight. Either modeling of forced rotor blade motion or modeling of aeroelastic unstability flutter are possible. The available analysis results consist in possibility to reflect, within the limits of a single model, upper and lower rotor blade loads and deformations, signal control links loads and deformations, flapping motion and aeroelastic blade approach. The numerical method and algorithm development results are presented. The stall flutter, flutter, coaxial-rotor system blade approach study results obtained in numerical experiments are given.

17th European Rotorcraft Forum 1991, Berlin

Conference Paper

englisch

21,0 x 29,7 cm, 18 Seiten

DGLR-Bericht, 1991, 1991-08, 17th European Rotorcraft Forum Proceedings; S.435-452; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

helicopters, mathematical models, rotors

Bestellbar

1991