Abstract This paper is devoted to the vibration of rotating flexible spacecraft. The maneuver of the spacecraft is modeled by a constant torque input acting on the hub. For the first time in this paper the equations of motion of flexible spacecraft are derived based on higher order sandwich panel theory (HSAPT). Hamilton's principle is used for driving the governing partial differential equations of motion. The generalized differential quadrature method (GDQ) is utilized to solve the partial differential equations of motion. The effect of different parameters on vibration of rotating flexible spacecraft appendage is investigated. It is also investigated the effect of these parameters on natural frequencies. The result of HSAPT and Euler Bernoulli theory is compared with each other. To show the accuracy the natural frequencies of recent paper are compared with the literature.

Abstract In this paper, the problem of vibration suppression of a smart composite plate with bonded piezoelectric patches is considered. A higher order plate model is used for finite element modeling of the plate and the PID controller is used to generate control voltage command to the piezo actuators from the piezo sensors data. Derived formulation and the control algorithm is implemented in a finite element (FE) code and the FE modeling results are verified using available results of previous studies. The effect of control gain on the vibration suppression characteristics is studied. Furthermore, since FE modeling reduces the order of the real problem, the problem of un-modeled residual modes on the so-called spillover effect is investigated.