Active Vibration Control of a Flexible Cantilever Beam by Applying Thermal Bending Moment

Murozono, Masahiko; Sumi, Seinosuke

doi:10.1177/1045389x9400500103

Cited by 15 publications

(14 citation statements)

References 10 publications

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“…Reference 22 deal with shape control by applied temperature. Murozono and Sumi (23) studied the active vibration control of a flexible cantilever beam by applying a transient thermal bending moment so that active control of the first bending mode is realised. Hsu et al (24) studied shape control of composite plates by bonded actuators with a high performance configuration.…”

Section: In the Ramjet Mode Operationmentioning

confidence: 99%

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Distributed parameter control arithmetic for an axisymmetrical dual-mode scramjet

Tao

Bao

2008

Aeronaut. j.

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A cross-sectional area J objective function k ratio of specific heats M Mach number P pressure S sensitivity T temperature W defined by Equation (20) x position co-ordinate along the axis of the channel Z defined by Equation (24) τ stagnation temperature rise ratio Subscripts 2 isolator entry 3 combustor entry 4 nozzle entry c core flow t total * at the critical point ABSTRACTDual-mode scramjet is one of the candidates for hypersonic flight propulsion system which will be used in wide range of flight Mach numbers from 4 to 12 or higher, wherein dual-mode scramjet should be well designed to be suitable for subsonic/supersonic combustion operation according to the flight conditions. Therefore this system is required to operate in a finite number of operational modes that necessitate robust, stable, and smooth transitions between them by which selective operability of supersonic/subsonic combustion modes and efficient combustor operation in these modes may be realised. A key issue in making mode transition efficient and stable is mode transition control. The major problem in mode transition control is the handling of the various flow and combustion coupling effects of dual-mode scramjet whose physical states are spatially coupled and whose governing equations are partial differential equations. Involving these distributed parameter issues, our basic idea is using the shape control theory to study the control problems of mode transition for dual-mode scramjet with the aim of achieving the desirable design properties and increasing control reliabilities. This specific approach is motivated by the promise of novel techniques in control theory developed in recent years. Concrete control arithmetic of this approach, such as shape control model, sensitivity analysis and gradient-based optimisation procedure, are given in this paper. Simulation results for an axisymmetric, wall-injection dual-mode scramjet show the feasibility and validity of the method.

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Section: In the Ramjet Mode Operationmentioning

confidence: 99%

“…(2) When M = 1 W = 1 (3) When M > 1 Equations (21) ~ (23) show that the denominators of and equal to at the critical point where W = 1, and unequal to zero in the whole region. Therefore, the singularity of the transonic flow equation is eliminated.…”

mentioning

confidence: 99%

Distributed parameter control arithmetic for an axisymmetrical dual-mode scramjet

Tao

Bao

2008

Aeronaut. j.

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“…Reference 39 deals with shape control by applied temperature. Murozono and Sumi (40) studied the active vibration control of a flexible cantilever beam by applying a transient thermal bending moment so that active control of the first bending mode is realised. Hsu et al (41) studied shape control of composite plates by bonded actuators with a high performance configuration.…”

Section: Sensitivity Equationmentioning

confidence: 99%

An idea of distributed parameter control for scramjet engines

Cui

Bao

2007

Aeronaut. j.

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Scramjet engines are used under extreme temperatures and with wide range of Mach numbers from 3 to 8 or higher and have shown different control properties from other airbreathing engines. New control problems involving distributed parameter control have been found concerning investigations of the control of scramjet engines whose physical states are spatially interacted and whose governing equations are partial differential equations. The work of this paper is based on the application of distributed parameter control conception to study the control problems of scramjet engines with the aim of achieving the desirable design properties and increasing control reliability. A new control idea based on shape control theory is put forward to realise the distributed parameter control of scramjet engines with the preconditions of proper space dimension and frequency-domain simplification. Simulation results and theoretic analysis for an axisymmetric, wall-injection scramjet engine show the feasibility and validity of the control idea.

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“…Experimental results reported in the paper show that with a simple lead compensation, damping ratio for the first vibrational mode of a cantilever beam is increased by more than nine times. Another work by Murozono and Sumi [5] also investigates active vibration control of a cantilever beam, but this time by heat input into the beam through the upper and lower surfaces, solely for creating a temperature gradient across the beam section. Foil strain gauges bonded on the surfaces are used as heat actuators.…”

Section: Introductionmentioning

confidence: 99%

Vibration Control Using Heat Actuators

Tuzcu¹

2016

WJM

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This paper focuses on theoretical investigation of active vibration control of a cantilever beam using heat actuation. The actuator is a thin metal bar rigidly bonded to the beam on one face and subject to heat input on the opposite face. The actuator then works like a piezoelectric actuator, and expands and contracts in response to applied heat. We assume that the actuator is insulated so that no heat is transferred to the beam, ensuring that the heat does not alter the beam's thermal state. To avoid necessity of cooling, we consider two actuators working together at the same spanwise location, one on the upper and one on the lower face of the beam. Then, the beam can be bent up and down by applying heat to the lower and upper actuators, respectively. The governing equations are partial differential equations for one-dimensional heat conduction of the actuators and the bending vibration of the beam with attached actuators. For an approximate solution, Rayleigh-Ritz method replaces the partial differential equations with a system of ordinary differential equations. A control model is obtained from a low-dimensional representation of the system, and used to design feedback control and observer by means of LQR and Kalman-Bucy filtering techniques. The control signal obtained is introduced into the plant model, a high-dimensional representation of the system, to mimic the true system as closely as possible. In a numerical application, the response of the beam to an initial excitation is simulated, which demonstrates that the heat actuators are in fact effective in active vibration control of the beam.

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Active Vibration Control of a Flexible Cantilever Beam by Applying Thermal Bending Moment

Cited by 15 publications

References 10 publications

Distributed parameter control arithmetic for an axisymmetrical dual-mode scramjet

Distributed parameter control arithmetic for an axisymmetrical dual-mode scramjet

An idea of distributed parameter control for scramjet engines

Vibration Control Using Heat Actuators

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