04.2 - Aerostructures Design, Structural Dynamics, Aeroelasticity
STUDY OF AEROELASTIC PROBLEM OF RUDDER SYSTEM WITH ELECTRIC ACTUATOR AND STRUCTURAL NONLINEARITIES
W. Qian¹, W.-Z. Feng, Dalian University of Technology, China; C.-X. Han¹, X.-Y. Ai¹; ¹Daian University of Technology, China
Stiffness of actuator is important for the aeroelastic behavior of rudder system which impacts the design of all-movable control surface of an aircraft. However, the conventional aeroelastic analyzing method took the supporting stiffness of a rudder system as a constant consciously or unconsciously, which led to mistakes in predicting the aeroelastic property of all-movable control surface. In this paper, the aeroelasticity problem for a complete rudder system with actual electric actuator and structural nonlinearities (e.g. free-play and friction) are studied. A Simulink model for a rudder system considering electromechanical part of actuator, elastic part of wing structure as well as free-play and friction nonlinear parts in the drive link is established. Through this model, the aeroelastic property of the all-movable control surface with rudder system can be obtained by time-domain simulation. Meantime, a test model with actual electric actuator is designed and manufactured, nonlinear dynamic test is carried out for estimation of nonlinear parameters including free-play angles and friction coefficients. Finally, the time-domain simulation results and dynamic test results are compared with each other for validating effectiveness of the established model. This paper gives a methodology for studying the aeroelastic property of rudder system supported by practical mechanism.