Multidisciplinary design optimization of a manned reentry mission considering trajectory and aerodynamic configuration

The purpose of this research is the optimal design of a reentry capsule configuration to minimize the mission cost which is usually modeled by minimizing reentry module mass (thermal protection system mass, propellant mass and structural mass). Multidisciplinary design optimization (MDO) is an important approach for the conceptual design of reentry capsule, because they are characterized by various disciplines that interact with one another. In this paper Trajectory, Aerodynamics, Structure, Thermal Protection System (TPS) and Deorbit Propulsion disciplines are modeled to optimize bi-conic configuration parameters. All At Once (AAO) frame work is developed and Genetic Algorithm (GA) is used to multidisciplinary conceptual design optimization of reentry mission with nonlinear constrains.