科研之友
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摘要
This paper describes the analytical development of a model representing a hingeless helicopter rotor equipped with trailing-edge flaps. The objective of the model is to provide an analytical tool that can be used to investigate major trends when specific physical parameters are changed, as well as to serve for the definition of parametric uncertainties in robustness analysis. The derivation follows a Lagrangian approach and includes the blade lagging, flapping, and torsional degrees of freedom. The aerodynamics of the blades is modeled using the thin-airfoil lifting-line theory and accounts for changes induced by the trailing-edge flaps on aerodynamic coefficients. The model is suited to cope with low-frequency dynamics such as lead-lag dynamics or rotor-blade tracking and balancing. It is validated against a Finite Element Method numerical model of the EC145 active hingeless rotor and against flight-test data provided by an EC145 demonstrator, both featuring trailing-edge flaps. The model shows great potential in representing accurately the aforementioned physical phenomena and provides a basis for studying the effects of physically meaningful parameters.
- 出版日期2013-10
