Optimal interplanetary rendezvous combining electric sail and high thrust propulsion system |
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| Authors: | Alessandro A Quarta Giovanni Mengali Pekka Janhunen |
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| Institution: | 1. Dipartimento di Ingegneria Aerospaziale, University of Pisa, I-56122 Pisa, Italy;2. Finnish Meteorological Institute, FIN-00101 Helsinki, Finland;1. School of Science, Nanjing University of Science and Technology, Nanjing, 210094, China;2. Institute of Launch Dynamics, Nanjing University of Science and Technology, Nanjing, 210094, China;3. State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, 29 Yudao Street, Nanjing, 210016, China;4. Department of Mechanical Engineering, York University, 4700 Keele Street, Toronto, Ontario, M3J 1P3, Canada;1. Purple Mountain Observatory, Chinese Academy of Sciences, Nanjing 210008;2. Key Laboratory of Space Object and Debris Observation, Purple Mountain Observatory, Chinese Academy of Sciences, Nanjing 210008;1. National Time Service Center, Chinese Academy of Sciences, Xi’an 710600;2. Graduate University of Chinese Academy of Sciences, Beijing 100049;3. School of Geodesy & Geomatics Engineering, Huaihai Institute of Technology, Lianyungang 222005;1. Laser and Photonics Engineering Group, School of Engineering, University of Lincoln, Brayford Pool, Lincoln, LN6 7TS, United Kingdom;2. Laser Engineering Group, School of Engineering, University of Liverpool, Liverpool, L69 3GH, United Kingdom |
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| Abstract: | The aim of this paper is to study, from a mission analysis point of view, the performance of a hybrid propulsion concept for a two-dimensional transfer towards a planet of the Solar System. The propulsion system is obtained by combining a chemical thruster, used for the phases of Earth escape and/or target planet capture, with an electric sail, which provides a continuous thrust during the heliocentric transfer. Two possible mission scenarios are investigated: in the first case the sailcraft reaches the target planet with zero hyperbolic excess velocity, thus performing a classical rendezvous mission in a heliocentric framework. In the second mission scenario, a given final hyperbolic excess velocity relative to the planet is tolerated in order to decrease the mission flight time. The amount of final hyperbolic excess velocity is used as a simulation parameter for a tradeoff study in which the minimum flight time is related to the total velocity variation required by the chemical thruster to accomplish the mission, that is, for Earth escape and planetary capture. |
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