Aerobraking is an efficient aeroassisted technique that has been used successfullyin recent Mars missions. However, trajectory design process is complicatedyet time consuming with multiple passes through the atmosphere. A simplebut effective design method to make this process easier is proposed. Firstly,perturbed classic element of orbit analysis is used to optimize of periapsis selection.After choosing the appropriate initial periapsis, an elaborate computationalmodel is developed to simulate the trajectory. Simulation results show asignificant reduction in the maximum control input and maximum heating rate.The method here can be used for reference to engineering application.
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