Multi-step optimization strategy for fuel-optimal orbital transfer of low-thrust spacecraft
Multi-step optimization strategy for fuel-optimal orbital transfer of low-thrust spacecraft
An effective method for the design of fuel-optimal transfers in two- and three-body dynamics is presented. The optimal control problem is formulated using calculus of variation and primer vector theory. This leads to a multi-point boundary value problem (MPBVP), characterized by complex inner constraints and a discontinuous thrust profile. The first issue is addressed by embedding the MPBVP in a parametric optimization problem, thus allowing a simplification of the set of transversality constraints. The second problem is solved by representing the discontinuous control function by a smooth function depending on a continuation parameter. The resulting trajectory optimization method can deal with different intermediate conditions, and no a priori knowledge of the control structure is required. Test cases in both the two- and three-body dynamics show the capability of the method in solving complex trajectory design problems
optimal control theory, trajectory optimization, low-thrust transfers, hybrid optimization methods
519-542
Rasotto, M.
17bab2a1-aa8a-45e2-9f00-846d0cde3256
Armellin, R.
61950d5c-3dcf-45f5-b391-7e8c6ffb8e6f
Di Lizia, P.
0f45735c-5c72-418f-945d-a5688f10c71e
2016
Rasotto, M.
17bab2a1-aa8a-45e2-9f00-846d0cde3256
Armellin, R.
61950d5c-3dcf-45f5-b391-7e8c6ffb8e6f
Di Lizia, P.
0f45735c-5c72-418f-945d-a5688f10c71e
Rasotto, M., Armellin, R. and Di Lizia, P.
(2016)
Multi-step optimization strategy for fuel-optimal orbital transfer of low-thrust spacecraft.
Engineering Optimization, 48 (3), .
(doi:10.1080/0305215X.2015.1025773).
Abstract
An effective method for the design of fuel-optimal transfers in two- and three-body dynamics is presented. The optimal control problem is formulated using calculus of variation and primer vector theory. This leads to a multi-point boundary value problem (MPBVP), characterized by complex inner constraints and a discontinuous thrust profile. The first issue is addressed by embedding the MPBVP in a parametric optimization problem, thus allowing a simplification of the set of transversality constraints. The second problem is solved by representing the discontinuous control function by a smooth function depending on a continuation parameter. The resulting trajectory optimization method can deal with different intermediate conditions, and no a priori knowledge of the control structure is required. Test cases in both the two- and three-body dynamics show the capability of the method in solving complex trajectory design problems
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Accepted/In Press date: 2 March 2015
e-pub ahead of print date: 20 April 2015
Published date: 2016
Keywords:
optimal control theory, trajectory optimization, low-thrust transfers, hybrid optimization methods
Organisations:
Astronautics Group
Identifiers
Local EPrints ID: 377353
URI: http://eprints.soton.ac.uk/id/eprint/377353
PURE UUID: 3fc3ac8a-e58e-424e-bb5f-ba0114a167a0
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Date deposited: 29 May 2015 13:16
Last modified: 14 Mar 2024 20:01
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Author:
M. Rasotto
Author:
P. Di Lizia
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