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Urrutxua Cereijo, Hodei and Pelaez Alvarez, Jesus and Baù, Giulio (2014). EDROMO: An accurate propagator for elliptical orbits in the perturbed two-body problem. In: "24th AAS/AIAA SpaceFlight Mechanics 2014 Meeting", 26-20 Ene 2014, Santa Fe, New Mexico (EEUU). pp. 1117-1136.
Title: | EDROMO: An accurate propagator for elliptical orbits in the perturbed two-body problem |
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Author/s: |
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Item Type: | Presentation at Congress or Conference (Article) |
Event Title: | 24th AAS/AIAA SpaceFlight Mechanics 2014 Meeting |
Event Dates: | 26-20 Ene 2014 |
Event Location: | Santa Fe, New Mexico (EEUU) |
Title of Book: | SpaceFlight Mechanics 2014 |
Date: | 2014 |
Subjects: | |
Faculty: | E.T.S.I. Aeronáuticos (UPM) |
Department: | Física Aplicada a la Ingeniería Aeronáutica [hasta 2014] |
Creative Commons Licenses: | Recognition - No derivative works - Non commercial |
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EDROMO is a special perturbation method for the propagation of elliptical orbits in the perturbed two-body problem. The state vector consists of a time-element and seven spatial elements, and the independent variable is a generalized eccentric anomaly introduced through a Sundman time transformation. The key role in the derivation of the method is played by an intermediate reference frame which enjoys the property of remaining fixed in space as long as perturbations are absent. Three elements of EDROMO characterize the dynamics in the orbital frame and its orientation with respect to the intermediate frame, and the Euler parameters associated to the intermediate frame represent the other four spatial elements. The performance of EDromo has been analyzed by considering some typical problems in astrodynamics. In almost all our tests the method is the best among other popular formulations based on elements.
Item ID: | 36866 |
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DC Identifier: | http://oa.upm.es/36866/ |
OAI Identifier: | oai:oa.upm.es:36866 |
Deposited by: | Memoria Investigacion |
Deposited on: | 03 Feb 2016 13:00 |
Last Modified: | 06 Jun 2016 13:00 |