P. Andersch, M. Hajek

An assessment of a frictional helicopter blade attachment with regard to its influence on the dynamics of the in-plane blade motion is presented. For detailed system analysis, a 3D finite element model with contact modeling has been created and validated using preexisting test data. Using the insights gained from 3D finite element simulations, a reduced order model suitable for dynamical simulations is derived and parameterized. Eventually, the reduced order model for the blade attachment is inserted into a hingeless dynamical rotor model with elastic coupling. The influence of the blade attachment on lead-lag dynamic behavior is investigated using the developed model and multiple configurations are compared to each other to identify the effects of the nonlinear blade attachment model on lead-lag frequency and damping ratio as well as elastic coupling prevalent in the hingeless rotor configuration.

41th European Rotorcraft Forum 2015

Conference Paper

englisch

21,0 x 29,7 cm, 14 Seiten

DGLR-Bericht, 2016, 2016-01, 41st European Rotorcraft Forum 2015; S.-; 2016; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

simulation;damping;dynamic characteristics;finite element method;friction factor;mathematical models;nonlinearity;rigid rotors;systems analysis;three dimensional models

Bestellbar

2016