Orbital Design for Multiple Flyby Missions

This paper presents a procedure to design multiple flyby missions. When the missions to observe space debris or near Earth asteroids (NEAs) are considered, it is more efficient to achieve many observations by a single spacecraft during the flight. Using the generating functions of canonical system, two-point boundary-value problem can be solved by function evaluations. Using this property, a strategy to optimize the multiple flyby sequence is proposed. This enables us to choose an optimal sequence among a long list of targets in which minimum fuel consumption is achieved. This paper focuses on the selection of sequence with pre-fixed interval time. The illustrated example using Hill two-body problem is shown.