A space station in the vicinity of the Moon can be exploited as a gateway for future human and robotic exploration of the solar system. The natural location for a space system of this kind is about one of the Earth–Moon libration points. The study addresses the dynamics during rendezvous and docking operations with a very large space infrastructure in an EML2 Halo orbit. The model takes into account the coupling effects between the orbital and the attitude motion in a circular restricted three-body problem environment. The flexibility of the system is included, and the interaction between the modes of the structure and those related with the orbital motion is investigated. A lumped parameter technique is used to represents the flexible dynamics. The parameters of the space station are maintained as generic as possible, in a way to delineate a global scenario of the mission. However, the developed model can be tuned and updated according to the information that will be available in the future, when the whole system will be defined with a higher level of precision.

Dynamical analysis of rendezvous and docking with very large space infrastructures in non-Keplerian orbits

Colagrossi, Andrea;Lavagna, Michèle
2018

Abstract

A space station in the vicinity of the Moon can be exploited as a gateway for future human and robotic exploration of the solar system. The natural location for a space system of this kind is about one of the Earth–Moon libration points. The study addresses the dynamics during rendezvous and docking operations with a very large space infrastructure in an EML2 Halo orbit. The model takes into account the coupling effects between the orbital and the attitude motion in a circular restricted three-body problem environment. The flexibility of the system is included, and the interaction between the modes of the structure and those related with the orbital motion is investigated. A lumped parameter technique is used to represents the flexible dynamics. The parameters of the space station are maintained as generic as possible, in a way to delineate a global scenario of the mission. However, the developed model can be tuned and updated according to the information that will be available in the future, when the whole system will be defined with a higher level of precision.
Circular restricted three-body problem; Flexible structure; Halo orbits; Large space station; Orbit-attitude dynamics; Aerospace Engineering; Space and Planetary Science
File in questo prodotto:
File Dimensione Formato  
COLAA02-18.pdf

Accesso riservato

Descrizione: Paper
: Publisher’s version
Dimensione 2.53 MB
Formato Adobe PDF
2.53 MB Adobe PDF   Visualizza/Apri
COLAA_OA_02-18.pdf

embargo fino al 27/09/2018

Descrizione: Paper open access
: Post-Print (DRAFT o Author’s Accepted Manuscript-AAM)
Dimensione 5.84 MB
Formato Adobe PDF
5.84 MB Adobe PDF Visualizza/Apri

I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.

Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11311/1053184
Citazioni
  • ???jsp.display-item.citation.pmc??? ND
  • Scopus 8
  • ???jsp.display-item.citation.isi??? 5
social impact