Multidisciplinary modeling and design of a space system

Author

Tester, John T. ; Robinson, David G.

Author_Institution

Dept. of Aeronaut. Eng., Wright-Patterson Air Force Base, Dayton, OH, USA

fYear

1993

fDate

1-3 Aug. 1993

Firstpage

446

Lastpage

449

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.<>

Keywords

aerospace control; aerospace simulation; dynamics; large-scale systems; ICBM; aerospace control; aerospace simulation; ballistic dynamics; bond graphs; concurrent engineering; large flexible space structure; minimum line-of-site error; missile plume; multidisciplinary modelling; optics; orbital dynamics; satellite; space shuttle capabilities; space system; vibrational analyses; Aerospace control; Aerospace simulation; Dynamics; Large-scale systems;

fLanguage

English

Publisher

ieee

Conference_Titel

Systems Engineering, 1991., IEEE International Conference on

Conference_Location

Dayton, OH, USA

Print_ISBN

0-7803-0173-0

Type

conf

DOI

10.1109/ICSYSE.1991.161172

Filename

161172