ANALYTICAL PREDICTION OF ROTOR FLAPPING ANGLES FOR USE IN HELICOPTER ROTOR STATE FEEDBACK CONTROL LAWS
High bandwidth flight control of helicopters can most likely be achieved when rotor disc tilt angles are used as feedback variables. This is called rotor state feedback. The aim of this paper is to investigate whether it is possible to use an analytical model to predict rotor disc tilt angles real-time in-flight. Conventional measurements such as rigid body states are inputs to the analytical model. The predicted angles should have a sufficient level of accuracy to be used as feedback variables. By doing so, rotor flapping does not have to be measured in-flight whilst rotor state feedback can still be applied. Flight test data of disc tilt angles is compared to a numerical simulation model and an analytical model for three manoeuvres. The test aircraft is the Bell 412 Advanced Systems Research Aircraft, operated by the National Research Council of Canada. Results indicate that the accuracy of the analytical model is probably high enough to be used in-flight to predict rotor disc tilt angles. The proposed analytical model contains many high-order coupling terms that are usually neglected in classical formulations.
Mark Voskuijl Marilena D. Pavel Daniel J. Walker Arthur W. Gubbels Binoy J. Manimala
Faculty of Aerospace Engineering Delft University of Technology Kluyverweg 1, 2629 HS Delft, The Net Department of Engineering University of Liverpool United Kingdom Institute for Aerospace Research National Research Council of Canada Canada AgustaWestland Yeovil United Kingdom
国际会议
南京
英文
1-19
2009-10-14（万方平台首次上网日期，不代表论文的发表时间）