Speaker
Dr
Ahmed Magdy Abdelaziz
(National Research Institute of Astronomy and Geophysics (NRIAG))
Description
In this paper, a mathematical model was developed to design and optimize interplanetary trajectories that include gravity assist. The method of patched conics and a solver of the Lambert problem transfers are used to cast the space trajectory design process as an optimization problem, subsequently solved by using MATLAB. This model has been tested to provide an overview of the processes involved in the interplanetary trajectory design and analysis of the Juno mission to Jupiter. The resulting mission analysis compared to the actual data published.
Primary author
Dr
Ahmed Magdy Abdelaziz
(National Research Institute of Astronomy and Geophysics (NRIAG))
