Abstract
The problem of interception of a rocket vehicle by optimal path at a preassigned point on the destination orbit by a commuter rocket vehicle launched from the peri centre of the launch orbit is solved by evaluating launch angle and orbital parameters of the transfer trajectory. The analysis is general in so far as it can be applied to any system non coaxial coplanar elliptic orbits under all gravitational fields. The equations have been reduced for axially aligned launch and destination orbits; various particular cases of coaxial orbits are analysed. Interception through Hohmann transfer trajectories have also been considered. The theory illustrated by taking a practical case of Earth Mars transfer.
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