B.R. Hanks, M.G. Gibert

Recent spacecraft have become very complex relative to their ancestors, and traditional approaches to structural dynamics design and development have begun to show inadequacies. In the future, spacecraft are envisioned which are assembled, deployed, or unfolded on-orbit in order to achieve necessary size while maintaining acceptable launch economy. In addition, onorbit assembly brings the possibility of spacecraft which may evolve in configuration over a period of years. This paper presents a brief explanatory overview of the technical nature and importance of structural dynamics and control for proposed future spacecraft structures. It also describes on-going test and analysis activities in a continuing interdisciplinary technology program in the Spacecraft Dynamics Branch of the NASA Langley Research Center to develop structural dynamics and control methods for application to future missions. Recent results from two lines of dynamics focused technology are described. They are Mission Dynamics, which focuses on structural dynamics prediction and verification, and ControlsStructures Interaction (CSI), which focuses on the potential performance benefits of integrated structures and controls systems. Both involve heavy use of laboratory experiments to validate analytical methods, as well as to develop/improve the test technology itself.

International Forum on Aeroelasticity and Structural Dynamics 1991, Aachen

Conference Paper

englisch

21,0 x 29,7 cm, 10 Seiten

DGLR-Bericht, 1991, 1991-06, International Forum on Aeroelasticity and Structural Dynamics 1991 Proceedings; S.265-274; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroelasticity

Bestellbar

1991