This paper presents a novel method for gust loads alleviation in a truss-braced wing in which an inerter-based device located in the truss structure is used to reduce peak-loads during a discrete ”1-cosine” gust. Recent studies have shown that gust loads and flutter are critical to the wing sizing and the overall performance of the truss-braced wing concept and it is understood that without additional efforts to mitigate against these effects the benefits of the truss-braced wing concept may be significantly reduced. It is demonstrated that the use of a tunable device known as a tuned inerter damper allows specific vibration modes to be targeted during the gust response, resulting in a reduction of 25% in root bending moment and 5% in root torque when tuned to the second global wing bending mode. Furthermore, it is noted that the force coefficients of the tuned inerter damper are small in comparison with the pure damper device and could be feasible within the scope of an aerospace application.
|Name||Journal of Aircraft|
|Publisher||American Institute of Aeronautics and Astronautics Inc. (AIAA)|
|Conference||AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, AIAA SciTech Forum|
|Abbreviated title||SciTech 2018|
|Period||8/01/18 → 12/01/18|