Vibration Reduction for Flexible Spacecraft Attitude Control Using PWPF Modulator and Smart Structures
Authors
Song, Gangbing
Agrawal, Brij N.
Subjects
Advisors
Date of Issue
1999
Date
March 1999
Publisher
Language
Abstract
This paper presents a new approach to vibration reduction of flexible spacecraft during attitude control by using Pulse Width Pulse Frequency (PWPF) Modulator for thruster firing and smart materials for active vibration suppression. The experiment was conducted on the Naval Postgraduate School (NPS)'s Flexible Spacecraft Simulator (FSS), which consists of a central rigid body and an L-shape flexible appendage. A pair of on-off thrusters are used to reorient the FSS. To actively suppress vibrations introduced to the flexible appendage, embedded piezoelectric ceramic patches are used as both sensors and actuators to detect and counter react to the induced vibration. For active vibration suppression using the piezoelectric ceramic patches, Positive Position Feedback (PPF) control targeting at the first two flexible modes of the FSS system is used. Experimental results demonstrate the effectiveness of the control strategy of PWPF modulation for attitude control and PPF for active vibration suppression.
Type
Conference Paper
Description
The article of record as published may be found at http://dx.doi.org/10.1109/AERO.1999.793157
Series/Report No
Department
Aeronautics and Astronautics
Organization
Identifiers
NPS Report Number
Sponsors
Funder
Format
Citation
Proceedings of IEEE Aerospace Conference, Snowmass, CO, March 1999.
Distribution Statement
Rights
This publication is a work of the U.S. Government as defined
in Title 17, United States Code, Section 101. As such, it is in the
public domain, and under the provisions of Title 17, United States
Code, Section 105, is not copyrighted in the U.S.