H.M. Kim, H.H. Doiron

This paper describes the random excitation design process which will be used with a free-decay time-domain technique for on-orbit modal identification of the Space Station Freedom (SSF) in a proposed flight experiment called the Modal Identification Experiment. Four linearly independent random forcing functions utilizing the attitude control system thrusters of the SSF were generated to identify closely-spaced modes. Attitudes and attitude rates of the SSF were maintained within their respective limits by introducing a different duty cycle for each thruster. Numerical simulations with realistic data acquisition errors demonstrated that all important structural modes can be excited and identified. Application of the baseline excitation to forced response modal identification methods which use frequency response functions. was also investigated.

International Forum on Aeroelasticity and Structural Dynamics 1991, Aachen

Conference Paper

englisch

21,0 x 29,7 cm, 8 Seiten

DGLR-Bericht, 1991, 1991-06, International Forum on Aeroelasticity and Structural Dynamics 1991 Proceedings; S.223-230; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroelasticity

Bestellbar

1991