A multiobjective, multidisciplinary design optimization of solid propellant based space launch vehicle

This paper proposes an approach for the multidisciplinary design & optimization of space launch vehicle, wherein the structure/mass, aerodynamics, propulsion and the trajectory system design are performed simultaneously using non-dominated sorting based genetic algorithm. The design problem is posed as an optimization problem in which all the discipline parameters constitute the design variables, which are used to optimize the multi-objective function, thereby resulting in an optimal overall design. The approach is demonstrated by application to the integrated design of a four stage solid launch vehicle. The mission is to deliver predefined payload to the low earth (circular) orbit. An existing, real world system has been used to validate the multistage launch vehicle system model.