On rocket performance, stability and control

The present work aims at the study of enhancing and improving rocket performance parameters. The rocket model used in the study is a nonlinear model with three degrees of freedom. The aerodynamic force characteristics are predicted using two methods analytically and numerically. Analytical aerodynamic characteristics are predicted by the component build-up method. Overall aerodynamic loads for an airframe are built up by summing up the aerodynamic characteristics of the major airframe components individually and then adding components interference factors. Numerical aerodynamic characteristics are predicted by using state of the art aerodynamic prediction code Missile DATCOM. The analytical aerodynamic model is implemented in rocket shape configuration optimization for best performance in terms of maximizing the lift over drag ratio to be achieved. Aerodynamics of the optimized rocket is predicted by Missile DATCOM and is implemented in the flight trajectory optimization. The two methods are evaluated and validated against known wind tunnel data. The optimal flight trajectory for maximum range is investigated with fuel and burning area ratios. The optimality is found by controlling the rocket through certain angle from the vertical at certain Mach number.