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Experimental verification attitude control techniques for flexible spacecraft slew maneuvers.

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Author
Hailey, Jeffrey A.
Date
1992-03
Advisor
Agrawal, Brij N.
Second Reader
Ross, I. Michael
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Abstract
The experimental verification of attitude control designs for flexible spacecraft is essential for reliable operation in space. The Flexible Spacecraft Simulator (FSS) at the Naval Postgraduate School is designed to test a variety of control designs. The experimental setup simulates pitch axis motion of a flexible spacecraft consisting of a rigid central body and a flexible appendage connecting a reflector. The primary actuators are a reaction wheel and thrusters. Angular position information is obtained with a rotary variable differential transformer (RVDT) and angular rate information is obtained by a solid state rate sensor. Two analytical models are derived: one based on cantilever modes, the other based on system modes. Both are the result of linearized equations of motion which assume small flexible displacements and rates. Slew maneuvers are conducted using four separate controllers. They are proportional-derivative (PD), torque profiles, bang-bang and optimal controllers. Techniques for state estimation are explored for the optimal controller since the standard estimation methods prove to be unsatisfactory. The sinusoidal torque profile delivers the best performance overall with the PD a close second. Momentum wheel desaturation with thrusters and thruster slew maneuvers are also performed. In all cases, experimental results are in close agreement with analytical predictions.
URI
http://hdl.handle.net/10945/23670
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Showing items related by title, author, creator and subject.

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    Experimental Verification of Attitude Control Techniques for Slew Maneuvers of Flexible Spacecraft 

    Hailey, J.; Sortun, C.; Agrawal, B.N. (1992);
    This paper presents experimental verification of modern and classical control laws on flexible spacecraft structures. The Flexible Spacecraft Simulator at the Naval Postgraduate School is designed to test a variety of ...
  • Thumbnail

    Vibration Reduction for Flexible Spacecraft Attitude Control Using PWPF Modulator and Smart Structures 

    Song, Gangbing; Agrawal, Brij N. (1999);
    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 ...
  • Thumbnail

    Rest-to-Rest Slew Maneuver of Three-Axis Rotational Flexible Spacecraft 

    Kim, J.J.; Agrawal, B.N. (2008);
    This paper presents a slew maneuver control design of three-axis rotational flexible spacecraft. The focus of the work is to investigate the nonlinear effect of the three axis maneuver for a flexible spacecraft when a ...
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