Multidisciplinary modeling and design of a space system

John T. Tester; David G. Robinson

doi:10.1109/icsyse.1991.161172

Multidisciplinary modeling and design of a space system

John T. Tester, David G. Robinson

Mechanical Engineering

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

1 Scopus citations

Abstract

The application of concurrent engineering approach to the design of a large flexible space structure is discussed. A full system model using bond graphs incorporating orbital and ballistic dynamics, controls, optics, and vibrational analyses is developed. Design of experiment techniques is used to analyze the entire system and determine the optimum set of design parameters. The objective of the design effort involved the simultaneous design of the control algorithm, structural characteristics, and optical geometry. The system size and mass were limited by current space shuttle capabilities. The satellite was required to track the missile plume of an ICBM with minimum line-of-site error and transmit the position data to earth.

Original language	English (US)
Title of host publication	IEEE International Conference on Systems Engineering
Publisher	Publ by IEEE
Pages	446-449
Number of pages	4
ISBN (Print)	0780301730, 9780780301733
DOIs	https://doi.org/10.1109/icsyse.1991.161172
State	Published - 1991
Event	1991 IEEE International Conference on Systems Engineering - Fairborn, OH, USA Duration: Aug 1 1991 → Aug 3 1991

Publication series

Name	IEEE International Conference on Systems Engineering

Other

Other	1991 IEEE International Conference on Systems Engineering
City	Fairborn, OH, USA
Period	8/1/91 → 8/3/91

ASJC Scopus subject areas

General Engineering

Access to Document

10.1109/icsyse.1991.161172

Cite this

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title = "Multidisciplinary modeling and design of a space system",

abstract = "The application of concurrent engineering approach to the design of a large flexible space structure is discussed. A full system model using bond graphs incorporating orbital and ballistic dynamics, controls, optics, and vibrational analyses is developed. Design of experiment techniques is used to analyze the entire system and determine the optimum set of design parameters. The objective of the design effort involved the simultaneous design of the control algorithm, structural characteristics, and optical geometry. The system size and mass were limited by current space shuttle capabilities. The satellite was required to track the missile plume of an ICBM with minimum line-of-site error and transmit the position data to earth.",

author = "Tester, {John T.} and Robinson, {David G.}",

year = "1991",

doi = "10.1109/icsyse.1991.161172",

language = "English (US)",

isbn = "0780301730",

series = "IEEE International Conference on Systems Engineering",

publisher = "Publ by IEEE",

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booktitle = "IEEE International Conference on Systems Engineering",

note = "1991 IEEE International Conference on Systems Engineering ; Conference date: 01-08-1991 Through 03-08-1991",

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T1 - Multidisciplinary modeling and design of a space system

AU - Tester, John T.

AU - Robinson, David G.

PY - 1991

Y1 - 1991

N2 - The application of concurrent engineering approach to the design of a large flexible space structure is discussed. A full system model using bond graphs incorporating orbital and ballistic dynamics, controls, optics, and vibrational analyses is developed. Design of experiment techniques is used to analyze the entire system and determine the optimum set of design parameters. The objective of the design effort involved the simultaneous design of the control algorithm, structural characteristics, and optical geometry. The system size and mass were limited by current space shuttle capabilities. The satellite was required to track the missile plume of an ICBM with minimum line-of-site error and transmit the position data to earth.

AB - The application of concurrent engineering approach to the design of a large flexible space structure is discussed. A full system model using bond graphs incorporating orbital and ballistic dynamics, controls, optics, and vibrational analyses is developed. Design of experiment techniques is used to analyze the entire system and determine the optimum set of design parameters. The objective of the design effort involved the simultaneous design of the control algorithm, structural characteristics, and optical geometry. The system size and mass were limited by current space shuttle capabilities. The satellite was required to track the missile plume of an ICBM with minimum line-of-site error and transmit the position data to earth.

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U2 - 10.1109/icsyse.1991.161172

DO - 10.1109/icsyse.1991.161172

M3 - Conference contribution

AN - SCOPUS:0026407225

SN - 0780301730

SN - 9780780301733

T3 - IEEE International Conference on Systems Engineering

SP - 446

EP - 449

BT - IEEE International Conference on Systems Engineering

PB - Publ by IEEE

T2 - 1991 IEEE International Conference on Systems Engineering

Y2 - 1 August 1991 through 3 August 1991

ER -

Multidisciplinary modeling and design of a space system

Abstract

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