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TECHNICAL PAPERS

Impact Isolation Limiting Performance Analysis for Three-Component Models

[+] Author and Article Information
Dmitry V. Balandin

Department of Computational Mathematics and Cybernetics,  Nizhny Novgorod State University, 23 Gagarin ave, Nizhny Novgorod, 603950, Russiabalandin@pmk.unn.runnet.ru

Nikolai N. Bolotnik

 Institute for Problems in Mechanics of the Russian Academy of Sciences, 101-1, prosp. Vernadskogo, Moscow, 119526, Russiabolotnik@ipmnet.ru

Walter D. Pilkey1

Mechanical and Aerospace Engineering Department,  University of Virginia, 122 Engineer’s Way, Charlottesville, VA 22904-4746wdp@virginia.edu

Sergey V. Purtsezov

Mechanical and Aerospace Engineering Department,  University of Virginia, 122 Engineer’s Way, Charlottesville, VA 22904-4746pusv@virginia.edu

1

Corresponding author.

J. Dyn. Sys., Meas., Control 127(3), 463-471 (Nov 17, 2004) (9 pages) doi:10.1115/1.1978914 History: Received May 12, 2004; Revised October 16, 2004; Accepted November 17, 2004

For the crashworthiness analysis of transport vehicles a three-component system that consists of a base, a container, and an object to be protected, connected by shock isolators, can be utilized as a model. An approach for a limiting performance analysis of shock isolation for such a model is proposed. This approach involves the reduction of the optimal control problem for the three-component system to an auxiliary optimal control problem for a two-component system. A detailed description of the technique for the determination of the absolute minimum of the performance index and construction of the optimal control is presented. A proposition that provides a mathematical substantiation for this technique is stated and proven. Example problems included in the paper demonstrate the effectiveness of the proposed technique.

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Copyright © 2005 by American Society of Mechanical Engineers
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Figures

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Figure 1

Three-body system model

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Figure 2

A model of the system with the object to be isolated having an internal mass

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Figure 3

Optimal time history of the control force applied to the lower torso (normalized by the mass of the lower torso)

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Figure 4

Optimal time history of the displacement of the lower torso relative to the ground

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Figure 5

Optimal time history of the displacement of the upper torso relative to the lower torso

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Figure 6

Regular component of the optimal absolute acceleration of the helicopter body

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