Stability derivatives and longitudinal dynamic stability analysis of a missile model

The stability derivatives of a missile model have been calculated and the response of a constrained missile model was examined. Behaviour of any airborne body after getting disturbed from the equilibrium position is of paramount importance for its stability analysis. The model of missile has been made using computer software. Stability derivatives of a missile have been calculated using computational fluid dynamics. To comprehend dynamic stability, analytical solution has been proposed using Newton's Second law and Small Disturbance Theory, assuming pure pitching motion. To visualize the behaviour of missile model, graphical solution has been taken out using computer code. For having an idea how it will work in real world, a cardboard model of the missile is made and has been analysed for different applied angles of attacks. At the end the analytical and experimental results have been compared. Major contributions of this work are calculation of a method to plot time history of angle of attack of a missile after some perturbation and conduction of experiment for purpose of comparison. In future, results can be validated for wind tunnel model which will be more accurate.