Experimental research on flexible beam modal control

Schaefer, B.; Holzach, H.

doi:10.2514/3.20028

Cited by 36 publications

(6 citation statements)

References 5 publications

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“…The L 2 -orthonormal eigen-modes m are given by (Ge´rardin and Rixen 1993;Scha¨fer and Holzach 1985):…”

Section: Numerical Approximation Of the Beam Equationmentioning

confidence: 99%

Diffusive wave-absorbing control: example of the boundary stabilization of a thin flexible beam

Montseny

2011

Journal of Vibration and Control

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In this paper we deal with the boundary control of the Euler-Bernoulli beam by means of wave-absorbing feedback. Such controls are based upon the reduction of reflected waves and involve long memory non-rational convolution operators resulting from specific properties of the system. These operators are reformulated under so-called diffusive input-output state-space realizations, which allow us to represent the global closed-loop system under the abstract form dX/dt ¼ AX with A the infinitesimal generator of a continuous semigroup. So, well-posedness and stability of the controlled system result from classical semigroup theory. Finite-dimensional approximations of the diffusive realizations are then studied, with the aim of providing implementable controls close to the ideal ones. Finally, significant numerical simulations are presented.

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“…The L 2 -orthonormal eigen-modes m are given by (Ge´rardin and Rixen 1993;Scha¨fer and Holzach 1985):…”

Section: Numerical Approximation Of the Beam Equationmentioning

confidence: 99%

Diffusive wave-absorbing control: example of the boundary stabilization of a thin flexible beam

Montseny

2011

Journal of Vibration and Control

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“…The free boundary of launcher is numbered as 24. Pulse thrusters can provide control force along x, y, z axes of launcher fixed coordinate, whose origin is (23,22), x-axis along firing direction is positive, positive direction of y-axis is perpendicular upward with x-axis in vertical plane, and positive direction of z-axis is determined using the right-handed inertial Cartesian coordinate system.…”

Section: Introductionmentioning

confidence: 99%

“…Meirovitch et al [19][20][21] developed the independent modal space control (IMSC) method for the vibration control of distributed systems. Experiments were also carried out to verify the feasibility of the modal control [21,22]. The IMSC method is selected as the framework of the control algorithms.…”

Section: Introductionmentioning

confidence: 99%

Design of active vibration control for launcher of multiple launch rocket system

Zhan

Rui

Bao

et al. 2011

Proceedings of the Institution of Mechanical Engineers, Part K:

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This study deals with analysis and design of active vibration control algorithm for the launcher of multiple launch rocket system (MLRS). The new method proposed is that guidance and control package are equipped on launcher, not rocket, to active control motion of launcher for the first time. It has interesting advantages as follows: (1) active vibration control is more competent, more pliable, and more realizable in engineering compared to passive vibration control.(2) The guidance and control package will not be destroyed. In this study, transfer matrix method of multibody system is used to build the controlled dynamic model of MLRS. This method does not need the global dynamic equations of system and has high computational rate. Independent modal space control method and optimal control theorem are applied to design control law with feedforward and feedback control loops. The modal filters are designed as the state estimator to obtain the modal coordinates and their derivatives. Modal disturbance force observer is designed to obtain modal disturbance force. Pulse-width pulse-frequency (PWPF) modulator is used to modulate the continue control force command into discrete control force in order to avoid high non-linear control action of pulse thruster. The control force provided by pulse thruster and parameters of PWPF are obtained. The numerical results indicate that control law determined by optimal theorem integrated with PWPF modulator achieves good performance in active vibration control of launcher. This study improves the performance of MLRS in resisting impact and provides theoretical support for accurate launch.

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“…The considered feedback controls will essentially be of the form (6), with the necessary additional hypothesis of asymptotic stability of the corresponding closed-loop system. Applying the inverse Laplace-transform to (6), we obtain the general expression in the time-domain :…”

Section: Feedback Controsls Under Considerationmentioning

confidence: 99%

“…The proof is straightforward using technical but elementary calculations. From (19), we may deduce by use of classical semigroup theory : 3 Analysis of the system For simplicity, we only consider feedbacks defined by (6), with the additional hypothesis : U = d = 0. So, the feedback matrix is reduced to : and the analysis of (13) is performed through the equivalent augmented system (14).…”

Section: Diffusive Representation Of the Feedbackmentioning

confidence: 99%