An indirect method to determine optimal low-thrust trajectories for the escape from Earth’s sphere of influence starting from Sun-Earth or Earth-Moon L2 is developed. The highly chaotic and non-linear dynamics of motion close to Lagrangian points challenges the remarkable precision of the indirect method: different approaches and improvements, such as multifield and possibly multiple-shooting methods, are identified and implemented to handle these numerical problems. The dynamic model considers 4-body gravitation, JPL ephemeris, and may include spherical harmonic models for Earth and Moon; solar radiation pressure is also considered. Results show single burn escape trajectories from Sun-Earth L2 and the relatively small influence of perturbations on C3 and propellant requirements. Single-burn and two-burn trajectories are required for escape from Earth-Moon L2, with large influence on performance by the relative positions of Sun and Moon.

Escape Trajectories from Lagrangian Points with Electric Propulsion / Mascolo, Luigi; Casalino, Lorenzo. - ELETTRONICO. - (2021). ((Intervento presentato al convegno 31st AAS/AIAA Space Flight Mechanics Meeting tenutosi a Virtual (ex Charlotte, North Carolina) nel 1-4 February, 2021.

Escape Trajectories from Lagrangian Points with Electric Propulsion

luigi mascolo;lorenzo casalino
2021

Abstract

An indirect method to determine optimal low-thrust trajectories for the escape from Earth’s sphere of influence starting from Sun-Earth or Earth-Moon L2 is developed. The highly chaotic and non-linear dynamics of motion close to Lagrangian points challenges the remarkable precision of the indirect method: different approaches and improvements, such as multifield and possibly multiple-shooting methods, are identified and implemented to handle these numerical problems. The dynamic model considers 4-body gravitation, JPL ephemeris, and may include spherical harmonic models for Earth and Moon; solar radiation pressure is also considered. Results show single burn escape trajectories from Sun-Earth L2 and the relatively small influence of perturbations on C3 and propellant requirements. Single-burn and two-burn trajectories are required for escape from Earth-Moon L2, with large influence on performance by the relative positions of Sun and Moon.
File in questo prodotto:
File Dimensione Formato  
AAS21-252.pdf

non disponibili

Descrizione: Articolo principale
Tipologia: 2a Post-print versione editoriale / Version of Record
Licenza: Non Pubblico - Accesso privato/ristretto
Dimensione 349.04 kB
Formato Adobe PDF
349.04 kB Adobe PDF   Visualizza/Apri   Richiedi una copia
Pubblicazioni consigliate

Caricamento pubblicazioni consigliate

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/11583/2897172