Dynamic stability derivatives of missile configurations (Theoretical evaluation)

Aircrafts and missiles for efficient nanoeuverability should have adequate stability and control characteristics. Both experimental and analytical techniques are available for the aircraft and missile designer to determine the stability derivatives. The experimental methods based on wind tunnel testing of models and free flight testing involve complicated equipment and measuring techniques and are subjected to several errors. Hence, there is a clear need for quicker method for prediction of the stability derivatives. The analytical description of the forces and moments acting on the missile following a small disturbances affects the aerodynamic forces and moments. These can be expressed as linear functions of the perturbations in the translational and angular velocities. The coefficients in these functions are called stability derivatives. The aerodynamic derivatives associated with translational velocities only are called static derivatives and the remaining dynamic derivatives. These, stability derivatives are the input for solving the dynamical problem of missile flight. The present paper deals with the determination of the stability derivatives of slender 13; finned missile configurations based on Bryson's analysis.