Design and implementation of the state estimator for trajectory following of an electromagnetic formation flight testbed
Name
312403744-MIT.pdf
Description
Full printable version
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6.39 MB
Format
Adobe PDF
Checksum (MD5)
7e12a3c4d2f322e67f0c269fc6eb88cc
Author(s)
Lee, Sang-il, S.M. Massachusetts Institute of Technology
Advisor(s)
Raymond J. Sedwick.
Date Issued
2008
Publisher
Massachusetts Institute of Technology
Abstract
Formation fight of multiple satellites is an attractive concept for achieving complicated space missions that are di±cult or impossible with a single monolithic satellite. Since traditional thrusters require propellant consumption for maintaining the formation of multiple satellites, one concern is the way of more efficiently generating thrust. A plausible concept for the alternative actuator is Electromagnetic Formation Flight (EMFF), which uses the electromagnetic force generated by superconducting magnets and the reaction torque generated by reaction wheels as the way to control position and attitude of each satellite respectively. Since all of the actuators in EMFF utilize solar energy and do not depend on consumables, the mission lifetime can be substantially increased. The Space Systems Laboratory at Massachusetts Institute of Technology has contributed to demonstrating the concept of EMFF by developing a testbed composed of two vehicles, and the mission for one moving vehicle to hold its position with respect to the other stationary vehicle on a plane was successfully achieved. In this thesis, it is pursued to experimentally show that the electromagnetic force is a su±cient control actuator for a trajectory following mission with a new state estimator designed for the mission. Firstly, the vehicle of the testbed is categorized into three subsystems of °ight computer, actuator, and measurement system, each of which is described in detail. Then, the new state estimator is designed with an extended Kalman filter algorithm, and the method to pre-filter erroneous ultrasound measurements is proposed. Its convergence is shown by simulation. Finally, the new state estimator is implemented in the testbed, and the experimental results for several kinds of sinusoidal commanded trajectories are presented, which shows the desired mission is successfully accomplished.
Description
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2008.
This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.
Includes bibliographical references (p. 65-67).
Subjects
Aeronautics and Astronautics.
MIT Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
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