Vibration Reduction for Flexible Spacecraft Following Momentum Dumping With/Without Slewing
Author:
Affiliation:
1. Lockheed Martin Advanced Technology Center, Palo Alto, California 94304
2. Georgia Institute of Technology, Atlanta, Georgia 30332
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Applied Mathematics,Electrical and Electronic Engineering,Space and Planetary Science,Aerospace Engineering,Control and Systems Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/2.4737
Reference20 articles.
1. Preshaping Command Inputs to Reduce System Vibration
2. Creating Time-Optimal Commands with Practical Constraints
3. Slewing Flexible Spacecraft with Deflection-Limiting Input Shaping
4. Command Shaping in Tracking Control of a Two-Link Flexible Robot
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