Abstract
Recently, with new trajectory design techniques and use of low-thrust propulsion systems, missions have become more efficient and cheaper with respect to propellant. As a way to increase the mission’s value and scientific return, secondary targets close to the main trajectory are often added with a small change in the transfer trajectory. As a result of their large number, importance and facility to perform a flyby, asteroids are commonly used as such targets. This work uses the Primer Vector theory to define the direction and magnitude of the thrust for a minimum fuel consumption problem. The design of a low-thrust trajectory with a midcourse asteroid flyby is not only challenging for the low-thrust problem solution, but also with respect to the selection of a target and its flyby point. Currently more than 700,000 minor bodies have been identified, which generates a very large number of possible flyby points. This work uses a combination of reachability, reference orbit, and linear theory to select appropriate candidates, drastically reducing the simulation time, to be later included in the main trajectory and optimized. Two test cases are presented using the aforementioned selection process and optimization to add and design a secondary flyby to a mission with the primary objective of 3200 Phaethon flyby and 25143 Itokawa rendezvous.
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Acknowledgments
The authors would like to thank Stefano Campagnola for his valuable inputs and comments during the course of this work and Jack Yeh for revising the text and providing comments on its improvement.
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Victorino Sarli, B., Kawakatsu, Y. Selection and trajectory design to mission secondary targets. Celest Mech Dyn Astr 127, 233–258 (2017). https://doi.org/10.1007/s10569-016-9724-x
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DOI: https://doi.org/10.1007/s10569-016-9724-x