Damping models for shear beams with applications to spacecraft wiring harnesses

Jeffrey L. Kauffman, George A. Lesieutre, Vít Babuška

Research output: Contribution to journalArticle

1 Citation (Scopus)

Abstract

Spacecraft wiring harnesses can fundamentally alter a spacecraft's structural dynamics, necessitating a model to predict the coupled dynamic response of the structure and attached cabling. Although a beam model including firstorder transverse shear can accurately predict vibration resonance frequencies, current time domain damping models are inadequate. For example, common proportional damping models result modal damping that depends unrealistically on the frequency. Inspired by a geometric rotation-based viscous damping model that provides frequency independent modal damping in an Euler-Bernoulli formulation, a viscous damping model with terms associated with the shear and bending angles is presented. The model provides modal damping that is approximately constant in the bending-dominated regime (low mode numbers), increasing by at most6%for a particular selection of bending and shear angle-based damping coefficients. In the shear-dominated regime (high mode numbers), damping values increase linearly with mode number and in proportion to the shear angle-based damping coefficient. A key feature of this shear beam damping model is its ready finite element implementation using only matrices commonly developed for an Euler-Bernoulli beam. Such an analysis using empirically determined damping coefficients generates damping values that agree well with existing spacecraft wiring harness cable data.

Original languageEnglish (US)
Pages (from-to)16-22
Number of pages7
JournalJournal of Spacecraft and Rockets
Volume51
Issue number1
DOIs
StatePublished - Jan 1 2014

Fingerprint

harnesses
wiring
Electric wiring
damping
Spacecraft
spacecraft
Damping
shear
viscous damping
coefficients
Euler-Bernoulli beams
dynamic structural analysis
dynamic response
Structural dynamics
cables
proportion
cable
Vibrations (mechanical)
Dynamic response

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

Cite this

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abstract = "Spacecraft wiring harnesses can fundamentally alter a spacecraft's structural dynamics, necessitating a model to predict the coupled dynamic response of the structure and attached cabling. Although a beam model including firstorder transverse shear can accurately predict vibration resonance frequencies, current time domain damping models are inadequate. For example, common proportional damping models result modal damping that depends unrealistically on the frequency. Inspired by a geometric rotation-based viscous damping model that provides frequency independent modal damping in an Euler-Bernoulli formulation, a viscous damping model with terms associated with the shear and bending angles is presented. The model provides modal damping that is approximately constant in the bending-dominated regime (low mode numbers), increasing by at most6{\%}for a particular selection of bending and shear angle-based damping coefficients. In the shear-dominated regime (high mode numbers), damping values increase linearly with mode number and in proportion to the shear angle-based damping coefficient. A key feature of this shear beam damping model is its ready finite element implementation using only matrices commonly developed for an Euler-Bernoulli beam. Such an analysis using empirically determined damping coefficients generates damping values that agree well with existing spacecraft wiring harness cable data.",
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Damping models for shear beams with applications to spacecraft wiring harnesses. / Kauffman, Jeffrey L.; Lesieutre, George A.; Babuška, Vít.

In: Journal of Spacecraft and Rockets, Vol. 51, No. 1, 01.01.2014, p. 16-22.

Research output: Contribution to journalArticle

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