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Optimal orbital rendezvous using high and low thrustOptimal control theory is used to examine a specific class of spacecraft trajectory problems where high- and low-thrust propulsion systems are utilized. These problems assume a spacecraft is in an established orbit about a planet. It is desired to execute an intercept of a pre-determined position in space in a specified amount of time using an optimal high-thrust program. The spacecraft then returns to the original orbit station using the low-thrust propulsion system in an optimal fashion. A minimum fuel solution is sought using the linearized equations of motion, known as the CW equations, which simplify the necessary computations. Solutions are obtained for problems with a fixed final time. However, for the time-open case, the optimal solution is for the final time to be infinite. With a weighted function of the final time in the performance index, a limited range of optimal single impulse solutions for the time -open case can also be found.
Document ID
19900059731
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Prussing, John E.
(Illinois, University Urbana, United States)
Larson, Catherine A.
(Illinois Univ. Urbana, IL, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
Astrodynamics
Report/Patent Number
AAS PAPER 89-354
Meeting Information
Meeting: AAS/AIAA Astrodynamics Conference 1989
Location: Stowe, VT
Country: United States
Start Date: August 7, 1989
End Date: August 10, 1989
Accession Number
90A46786
Funding Number(s)
CONTRACT_GRANT: NAG3-805
Distribution Limits
Public
Copyright
Other

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