The paper presents a new approximate method for the estimation of minimum DeltaV and propellant consumption for electric propulsion missions to Near-Earth asteroids. The method is purely algebraic and therefore very fast, as integration of the equations of motion is not required. It is based on the decomposition of the propulsive effort into basic burns; each burn has a specific purpose (i.e., change of perihelion or aphelion distance). The effects and the cost of the basic burn arcs are evaluated for almost-circular orbits with small inclination changes. An approximate suboptimal control law, which was initially developed for continuous thrust maneuvers, is employed. In general, results show a very good accuracy, with errors below 10-15% of the propellant consumption. Larger errors occur for specific combinations of the orbital parameters, when the plane change maneuver does not follow the expected scenario. Suggestions for improvements of the estimation method are highlighted, as the analysis of the results gives insight about the characteristics of missions to different NEAs.

Fast Estimation Method for Trajectories to Near-Earth Asteroids / Mascolo, Luigi; Casalino, Lorenzo; Bosa, Alessandro. - ELETTRONICO. - 171:(2019), pp. 3091-3100. ((Intervento presentato al convegno 2019 AAS/AIAA Astrodynamics Specialist Conference tenutosi a Portland, ME nel 11-16 Agosto 2019.

Fast Estimation Method for Trajectories to Near-Earth Asteroids

mascolo luigi;lorenzo casalino;BOSA, ALESSANDRO
2019

Abstract

The paper presents a new approximate method for the estimation of minimum DeltaV and propellant consumption for electric propulsion missions to Near-Earth asteroids. The method is purely algebraic and therefore very fast, as integration of the equations of motion is not required. It is based on the decomposition of the propulsive effort into basic burns; each burn has a specific purpose (i.e., change of perihelion or aphelion distance). The effects and the cost of the basic burn arcs are evaluated for almost-circular orbits with small inclination changes. An approximate suboptimal control law, which was initially developed for continuous thrust maneuvers, is employed. In general, results show a very good accuracy, with errors below 10-15% of the propellant consumption. Larger errors occur for specific combinations of the orbital parameters, when the plane change maneuver does not follow the expected scenario. Suggestions for improvements of the estimation method are highlighted, as the analysis of the results gives insight about the characteristics of missions to different NEAs.
File in questo prodotto:
File Dimensione Formato  
AAS 19-761.pdf

non disponibili

Tipologia: 2a Post-print versione editoriale / Version of Record
Licenza: Non Pubblico - Accesso privato/ristretto
Dimensione 261.73 kB
Formato Adobe PDF
261.73 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: http://hdl.handle.net/11583/2746548