Aeroelastic Control of Smart Composite Plate with Delaminations

Abstract

In this paper, aeroelastic performance of smart composite wing in the presence of delaminations is investigated. A control system is designed to enhance the dynamic stability of the delaminated composite wing. The refined higher order theory for analyzing an adaptive composite plate in the presence of delaminations is used. The theory accurately captures the transverse shear deformation through the thickness, which is important in anisotropic composites, particularly in the presence of discrete actuators and sensors and delaminations. The effects of delamination on the aeroelastic characteristics of composite plates are investigated. An active control system is designed to redistribute the loads and to minimize the effect of delamination. The pole placement technique is applied to design the closed loop system by utilizing piezoelectric actuators. Due to delamination, the significant changes in the natural frequencies of the lower modes are observed. This causes the reduction on the flutter speed of the delaminated plate model. The aeroelastic control results show that controller makes the delaminated plate model behave like a normal plate. The controller also reduces a significant amount of the root mean square values of the gust response due to gust.

Recent progress on flutter‐based wind energy harvesting

“…Flutter is a common topic in the aviation field. For aviation structures, the phenomenon of flutter must be avoided 100–102 . The energy harvesting structure can be regarded as an energy dissipation mechanism 103 .…”

“…For aviation structures, the phenomenon of flutter must be avoided. [100][101][102] The energy harvesting structure can be regarded as an energy dissipation mechanism. 103 The application of energy harvesters to the research on the integration of vibration suppression and energy harvesting of aircraft structures is very promising.…”

Aeroelastic analysis and flutter control of wings and panels: A review

“…It was found that the controlled system can achieve a significant increase in the critical flutter aerodynamic pressure. Nam et al 266 carried out the active flutter control of composite laminated plates with delamination using the piezoelectric actuators and sensors, in which the controller was designed by the proportional feedback control algorithm. Moreover, Li 267 used the proportional and acceleration feedback control to design a controller to suppress the flutter of panels.…”

Adaptive Structural Control Experiment Using Recursive System Identification

“…In those cases, the designed control scheme based on the nominal system may significantly degrade the performance or sometimes even destabilize the closed-loop system. Recently, there has been considerable interest in the field of structural damage or failure (Li et al, 1999;Sundaresan et al, 2002;Tseng and Naidu, 2002), especially for the case of crack initiation (Saavedra and Cuitino, 2001;Rajic et al, 2002) or delamination (Nam et al, 2000). Also equal research momentum has been focused on dealing with those problems by adopting several control design methodologies Boskovic and Mehra, 2002;Song et al, 2002).…”