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Finite element method for optimal guidance of an advanced launch vehicleA temporal finite element based on a mixed form of Hamilton's weak principle is summarized for optimal control problems. The resulting weak Hamiltonian finite element method is extended to allow for discontinuities in the states and/or discontinuities in the system equations. An extension of the formulation to allow for control inequality constraints is also presented. The formulation does not require element quadrature, and it produces a sparse system of nonlinear algebraic equations. To evaluate its feasibility for real-time guidance applications, this approach is applied to the trajectory optimization of a four-state, two-stage model with inequality constraints for an advanced launch vehicle. Numerical results for this model are presented and compared to results from a multiple-shooting code. The results show the accuracy and computational efficiency of the finite element method.
Document ID
19920057267
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Hodges, Dewey H.
(NASA Langley Research Center Hampton, VA, United States)
Bless, Robert R.
(NASA Langley Research Center Hampton, VA, United States)
Calise, Anthony J.
(NASA Langley Research Center Hampton, VA, United States)
Leung, Martin
(Georgia Institute of Technology Atlanta, United States)
Date Acquired
August 15, 2013
Publication Date
June 1, 1992
Publication Information
Publication: Journal of Guidance, Control, and Dynamics
Volume: 15
Issue: 3 Ma
ISSN: 0731-5090
Subject Category
Cybernetics
Accession Number
92A39891
Funding Number(s)
CONTRACT_GRANT: NAG1-939
Distribution Limits
Public
Copyright
Other

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