Special Earth-Mars transfers that exploit both chemical and solar electric propulsion are investigated in this work. A dedicated launch strategy via Soyuz is considered. Firstly, a high-thrust, low-Isp impulse is used to place the spacecraft onto an Earth-escape trajectory, possibly performing a lunar swingby. Then, an heliocentric rendezvous with Mars is achieved via low-thrust, high-Isp propulsion, followed by a ballistic capture leading to a final, low-altitude orbit around Mars. Hybrid propulsion transfers outperform chemical transfers (Hohmann) in terms of propellant consumption. Furthermore, a few considerations at system level are also proposed.

Hybrid Propulsion Transfers for Mars Science Missions

TOPPUTO, FRANCESCO;MASSARI, MAURO
2013

Abstract

Special Earth-Mars transfers that exploit both chemical and solar electric propulsion are investigated in this work. A dedicated launch strategy via Soyuz is considered. Firstly, a high-thrust, low-Isp impulse is used to place the spacecraft onto an Earth-escape trajectory, possibly performing a lunar swingby. Then, an heliocentric rendezvous with Mars is achieved via low-thrust, high-Isp propulsion, followed by a ballistic capture leading to a final, low-altitude orbit around Mars. Hybrid propulsion transfers outperform chemical transfers (Hohmann) in terms of propellant consumption. Furthermore, a few considerations at system level are also proposed.
Spaceflight Mechanics 2013
ADVANCES IN THE ASTRONAUTICAL SCIENCES
978-0-87703-597-8
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Utilizza questo identificativo per citare o creare un link a questo documento: http://hdl.handle.net/11311/713359
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