Manipal Journal of Science and Technology


In this paper, a modified predictor-corrector method is explored to get a constrained optimal trajectory for Mars entry phase. The method uses a parameterized bank angle equation, which is given in terms of specific energy and hence enabling a three-dimensional trajectory optimization. The reference trajectory needed for computation of bank angle in each guidance cycle is obtained using the steepest descent method. Variation in bank angle is restricted. Typical entry path constraints, heat rate, dynamic pressure, and load factor were successfully imposed while minimizing the terminal position and velocity errors.

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