In this paper, the aeroelastic response of a hingeless rotor blade in hover is investigated. The hingeless rotor blade was modeled by using the geometrically exact fully intrinsic beam equations combined with the quasi-steady aerodynamic loads and uniform inflow. The partial differential equations were discretized by using the time-space scheme. A particular blade with precone angles was considered, and the stability boundaries of this blade were determined. Then the aeroelastic response of the blade for stable and unstable regions was determined. It was found that the blade experiences different types of responses depending on the system parameters. A more comprehensive study is required to characterize the effective parameters and what type of response a blade may experience in the postaeroelastic instability region.
|Journal||Journal of Aerospace Engineering|
|Early online date||28 May 2019|
|Publication status||Published - 1 Sep 2019|