Observatorio de I+D+i UPM

Descripción
The minimum-time, low-constant-thrust, same circular orbit rendezvous problem is studied using a relative motion description of the system dynamics. The resulting Optimal Control Problem in the thrust orientation angle is formulated using both the Direct and Indirect method. An extensive set of test cases is numerically solved with the former, while perturbation techniques applied to the later allow to obtain several approximate solutions and provide a greater insight on the underlying physics. These results show that the structure of the solutions undergoes fundamental changes depending on the value of the non-dimensional thrust parameter.missions. To this end, an optimal control formulation based in Dromo and a direct transcription method is used to solve several LEO-GEO and escape from Earth problems; the obtained results clearly show the suitability of this orbital propagation for such purposes.
Internacional	Si
Nombre congreso	25th AAS/AIAA Space Flight Mechanics Meeting
Tipo de participación	960
Lugar del congreso	Williamsburg, Virginia (EEUU)
Revisores	Si
ISBN o ISSN	1081-6003
DOI
Fecha inicio congreso	11/01/2015
Fecha fin congreso	15/01/2015
Desde la página	1783
Hasta la página	1801
Título de las actas	Advances in the Astronautical Sciences Volume 155, Spaceflight Mechanics Subseries

Esta actividad pertenece a memorias de investigación

• Autor: Juan Luis Gonzalo Gomez (UPM)
• Autor: Claudio Bombardelli (UPM)

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