Analysis and design optimization of solid rocket motors in viscous flows

The objective of this study is to develop a design tool that can be used in viscous flows. The flow analysis is based on the axisymmetric Navier–Stokes and k–ɛ turbulence equations. These coupled equations are solved using an explicit finite difference method. The accuracy of the analysis code is validated for viscous flows in solid rocket motor combustion chamber and nozzle. The gradient-based numerical optimization model is used to maximize the thrust of solid rocket motor under a constraint of propellant weight. The sensitivity analysis that measures the response of the flow with respect to a geometry perturbation is calculated by finite differencing. The optimization of design study employs a commercial optimization package. The performance of design optimization method is tested in solid rocket motor combustion chamber and nozzle design.

► A flow analysis code is developed to simulate the viscous flow in rocket motors.
► Results of the developed code provides good accuracy with the experimental data.
► The gradient-based numerical optimization model is developed to maximize thrust.
► The sensitivity derivatives are obtained by finite difference method.
► Maximum improvement in thrust is achieved by simultaneous design optimization.