An aeroelastic simulation of a stiff in-plane hingeless rotor in forward flight is conducted to evaluate the feasibility of reducing lagwise root loads via an embedded absorber within the blade. A finite element analysis based on a moderate deflection beam model is employed to capture the flap, lag, and torsion deflections of the rotor blade. The mass-spring-damper absorber system is simulated as a one-degree-of-freedom rigid body with chordwise motion. By using the Hamilton principle, system equations of motion are derived based on the generalized force formulation. Dynamic responses are calculated to investigate the potential of the absorber for in-plane loads reduction. Parametric studies are conducted to explore the influence of the absorber on the dynamic characteristics of the rotor blade. From the aeroelastic analysis of the blade-absorber system, results indicate that placing an embedded absorber in the blade chordwise direction can decrease the 1 and 2/rev lagwise root bending moments by about 50 and 90%, respectively, under large load states. The effects of absorber frequency, absorber damping, chordwise position of the absorber, rotor thrust, forward speed, and trim condition are also studied.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering