Observatorio de I+D+i UPM

Descripción
The tight relationship between the stop-condition of a numerical integrator and the resulting accuracy of regularized orbit propagators is addressed. It is noted that the use of events as a means to halt the numerical orbit propagation introduces timing or phasing errors in formulations involving a Sundman transformation. The fundamentals of this timing error are described, along with the mechanisms that produce this apparent loss in the achievable accuracy. This behavior is linked to the dynamical instabilities of the orbital motion. Examples are provided to support that the purely geometrical description provided by regularized methods is typically orders of magnitude more accurate than when the timing error is taken into account.
Internacional	Si
Nombre congreso	26th AAS/AIAA Space Flight Mechanics Meeting
Tipo de participación	960
Lugar del congreso	Napa, California
Revisores	Si
ISBN o ISSN	1081-6003
DOI
Fecha inicio congreso	14/02/2016
Fecha fin congreso	18/02/2016
Desde la página	1
Hasta la página	14
Título de las actas	Advances in the Astronautical Sciences

Esta actividad pertenece a memorias de investigación

• Autor: Claudio Bombardelli (UPM)
• Autor: Jesus Pelaez Alvarez (UPM)
• Autor: Hodei Urrutxua (University of Southampton)

• Creador: Grupo de Investigación: Dinámica Espacial (SDG-UPM)
• Departamento: Física Aplicada a Las Ingenierías Aeronáutica y Naval