Dynamic Loads Analysis And Driving Mechanism Optimum Design Of Active Trailing Edge Rotor

Helicopter is widely used in both civil and military areas for rescuing, transporting,anti-submarine and reconnaissance, due to its high efficiency in hover and other capabilities, such as vertical takeoff and landing, slow-speed forward flight and less limitation on taking off and landing.Helicopter suffers serious vibration problem because the long flexible blades of rotor work in complex environment of aerodynamics and centrifugal forces.There are mainly two methods that have been adopted in rotor vibration control, including passive methods and active methods. Active trailing-edge flap is one of the active methods, and it has the advantages of higher efficiency of vibration control and wider range of frequencies, therefore active trailing-edge flap was selected and studied in this thesis. Several actuation mechanisms have been proposed in the past research, while the rhombic frame is more compacter in structure and higher efficiency in actuation, so the rhombic frame was designed and analyzed in this thesis.Based on the research achievements of the group, an aerodynamic-elastic coupling analysis model with improved 2-D airfoil aerodynamic model was established, Particle Swarm Optimization(PSO) and PSO-Genetic Algorithm were utilized to optimize the control law of the flap,the placement and size parameters were analyzed and optimized. Base on the analysis results, design and optimization works for the rhombic frame were conducted using APDL parametrization design language. The geometrical parameters of the frame including length, angle and thickness of the sloping arm were optimized, finally the optimized design was presented.