nro14_200305

nro14_200305 - Electromagnetic Formation Flight Progress...

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Electromagnetic Formation Flight Progress Report: May 2003 Submitted to: Lt. Col. John Comtois Technical Scientific Officer National Reconnaissance Office Contract Number: NRO-000-02-C0387-CLIN0001 MIT WBS Element: 6893087 Submitted by: Prof. David W. Miller Space Systems Laboratory Massachusetts Institute of Technology
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O VERVIEW Description of the Effort The Massachusetts Institute of Technology Space Systems Lab (MIT SSL) and the Lockheed Martin Advanced Technology Center (ATC) are collaborating to explore the potential for an Electro-Magnetic Formation Flight (EMFF) system applicable to Earth-orbiting satellites flying in close formation. Progress Overview At MIT, work on EMFF has been pursued on two fronts: the MIT conceive, design, implement and operate (CDIO) class, and the MIT SSL research group. This report summarizes recent progress made in the MIT CDIO class with regards to system dynamic modeling, linear control design, and closed-loop control implementation on the electromagnetic formation flight testbed being designed and built in the class. First the testbed control requirements and experimental testing plan (“test cases”) are presented, and the linearized dynamic model of the testbed system is discussed. Then the linear control design methodology is reviewed, and the resulting control gains specific to each test case are presented. Finally, successful closed-loop dynamic results are presented for test cases 1a and 1b.
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EMFFORCE OPS MANUAL Space Systems Product Development – Spring 2003 Massachusetts Institute of Technology 1 Dept of Aeronautics and Astronautics A Control Algorithm Development A.1 Control Requirements Electromagnets and reaction wheels are used to provide the forces and torques necessary to control position and attitude of the vehicles. The interaction between electromagnets of different vehicles can be controlled to either attract or repel the vehicles. The reaction wheels can rotate either clockwise or counterclockwise, providing control to either accelerate or decelerate the vehicles rotationally. Varying the current through the magnets and changing the speed of the wheels control the actuators. Controlling these accurately allows for maneuvering the vehicles and disturbance rejection. The responsibility of the control team was to build a robust controller for the project that will command maneuvers and provide disturbance rejection. The controller is located on the avionics computer, and processes metrology inputs in order to calculate the necessary commands to send to the actuators. This is depicted in the block diagram in Figure A.1-A. Figure A.1-A: Block Diagram of Controller The control team designed controllers to meet the following requirements, derived from the requirements document.
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This note was uploaded on 11/08/2011 for the course AERO 16.810 taught by Professor Olivierdeweck during the Winter '07 term at MIT.

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nro14_200305 - Electromagnetic Formation Flight Progress...

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