Passive Gust Load Alleviation In a Truss-Braced Wing Using an Inerter-Based Device

Abstract

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.

Real-Time Hybrid Testing of Strut-Braced Wing Under Aerodynamic Loading Using an Electrodynamic Actuator

“…Fig. 3 Influence of numerical substructure on the lead/lag behaviour of the controller-actuator subsystem L a m a s 6 ((…”

“…Recently, it has been proposed that the truss could serve not simply as static support, but also to reduce dynamic gust loads by inserting a vibration absorber into one of the struts, either as a traditional suspension system [5], or as an inerter-based device [6]. The geometric nonlinearities stemming from the greater flexibility associated with HAR wings, however, mean that the traditional modelling methods, based on linear elastic and aerodynamic theory, are not necessarily adequate, and can lead to conservative structural designs [7], and to inaccurate estimations of the flutter speeds [3,8].…”