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Design of a LQR Controller of Reduced Inputs for Multiple Spacecraft Formation FlyingRegarding multiple spacecraft formation flying, the observation is made that control thrust need only be applied coplanar to the local horizon to achieve complete controllability of a two-satellite formation. Without the need for zenith-nadir (radial) thrust, simplifications and reduction of the weight of the propulsion system may be accomplished. This work focuses on the validation of this radial-excluding control system on its own merits, and in comparison to a related system which does provide thrust parallel to the orbital radius. Simulations are performed using commercial ODE solvers to propagate the Keplerian dynamics of a controlled satellite relative to an uncontrolled, leader satellite. The conclusion is drawn that, despite the exclusion of the radial thrust axis, the remaining control thrust available still provides enough control to design a gain matrix of adequate performance using linear-quadratic regulator (LQR) techniques.
Document ID
20010049373
Acquisition Source
Legacy CDMS
Document Type
Preprint (Draft being sent to journal)
Authors
Starin, Scott R.
(NASA Goddard Space Flight Center Greenbelt, MD United States)
Yedavalli, R. K.
(Ohio State Univ. Columbus, OH United States)
Sparks, Andrew G.
(Air Force Research Lab. Wright-Patterson AFB, OH United States)
Bauer, Frank H.
Date Acquired
August 20, 2013
Publication Date
January 1, 2001
Subject Category
Spacecraft Design, Testing And Performance
Meeting Information
Meeting: 2001 American Control Conference
Country: United States
Start Date: June 25, 2001
End Date: June 27, 2001
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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