Uniform damping control: discretization and optimization

Silverberg, Larry; Redmond, James M.; Weaver, L.

doi:10.1016/0307-904x(92)90064-a

Cited by 4 publications

(4 citation statements)

References 4 publications

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“…When t q >tg, then event E 2 becomes a passive constraint since E\ C\E 2 = EI in Eq. (7). Similarly, when t q <t q , then event E\ becomes a passive constraint since E\ Pi E 2 = E 2 in Eq.…”

Section: Modification Of the Impulsive Control Forcementioning

confidence: 92%

“…Toward this end, the spacecraft is divided into subdomains, each containing a discrete control force at its mass center. 7 Integrating Eq. (26) over each subdomain, we obtain …”

Section: Mode Preserving Discrete Control Forcesmentioning

confidence: 99%

“…8 The coupling coefficients can approximate the Kronecker delta function, that is, c rs d rs , where d rr = 1 and d rs = 0 for r ^ s. Note that the diagonalization of the coupling coefficients provides a fuel optimal basis for the optimal selection of the locations of the control forces and of the subdomain masses m r . 7 1) The impulsive damping control algorithm is independent of spacecraft stiffness.…”

Section: Uniformly Distributed Impulsive Damping Using Discrete Contrmentioning

confidence: 99%

“…Similarly, when t q <t q , then event E\ becomes a passive constraint since E\ Pi E 2 = E 2 in Eq. (7). Passive constraints are avoided by selecting identical pulse times for EI and E 2 .…”

Section: Modification Of the Impulsive Control Forcementioning

confidence: 99%

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Light impulsive damping of spacecraft exhibiting normal mode behavior

Silverberg

1992

Journal of Guidance, Control, and Dynamics

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This paper develops an impulsive damping control algorithm suitable for spacecraft. The fuel optimal solutions to the problem of damping the motion of spacecraft consists of impulsive control forces applied at repeated instances in time. The instances in time occur when the spacecraft undergoes maximum absolute velocities and minimum absolute displacements. This paper approximates impulses by short duration pulses. Maximum absolute velocities and minimum absolute displacements are then approximated by transient values of their respective standard deviations. Impulsive damping is achieved by applying either a large single pulse or smaller repeated pulses. A near fuel optimal mode preserving impulsive damping control algorithm is developed next. The algorithm exhibits the following properties: 1) the impulsive damping control algorithm is independent of spacecraft stiffness, 2) the associated control forces are proportional to spacecraft inertia, and 3) the impulsive damping control algorithm is decentralized. The impulsive damping of a cantilever beam demonstrates the results.

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Section: Modification Of the Impulsive Control Forcementioning

confidence: 92%

“…Toward this end, the spacecraft is divided into subdomains, each containing a discrete control force at its mass center. 7 Integrating Eq. (26) over each subdomain, we obtain …”

Section: Mode Preserving Discrete Control Forcesmentioning

confidence: 99%

Section: Uniformly Distributed Impulsive Damping Using Discrete Contrmentioning

confidence: 99%

“…Similarly, when t q <t q , then event E\ becomes a passive constraint since E\ Pi E 2 = E 2 in Eq. (7). Passive constraints are avoided by selecting identical pulse times for EI and E 2 .…”

Section: Modification Of the Impulsive Control Forcementioning

confidence: 99%

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Light impulsive damping of spacecraft exhibiting normal mode behavior

Silverberg

1992

Journal of Guidance, Control, and Dynamics

Self Cite

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Uniform Damping and Stiffness Control of Structures With Distributed Actuators

Washington

Silverberg

1997

Journal of Dynamic Systems, Measurement, and Control

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The research in this paper introduces an algorithm for uniformly damping and stiffening structures using distributed actuators. Inherent in this algorithm is the ability to eliminate structural biases, which can cause steady state error. The method involves the utilization of modal techniques to calculate the proportional, integral, and derivative gains in a feedback control law. The gains are calculated by first converting the system into the modal domain, second by employing the principles of uniform damping and stiffening to the system in the modal domain, and finally by converting that system back into the physical domain. The beauty of this technique lies in the fact that even though the principles of modal control are used in gain setting, no modal information is needed in the fined control law. The theory is validated by simulations and is illustrated in an example. Since a modal approach and distributed actuation is utilized, the benefit to active control and adaptive structures is discussed.

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Autonomous Coordination of Aircraft Formations Using Direct and Nearest-Neighbor Approaches

Silverberg

Levedahl

2005

Journal of Aircraft

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Uniform damping control: discretization and optimization

Cited by 4 publications

References 4 publications

Light impulsive damping of spacecraft exhibiting normal mode behavior

Light impulsive damping of spacecraft exhibiting normal mode behavior

Uniform Damping and Stiffness Control of Structures With Distributed Actuators

Autonomous Coordination of Aircraft Formations Using Direct and Nearest-Neighbor Approaches

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