No abstract

Static and dynamic stability are the most important phenomena for stable flight atmospheric motion of spin and fin stabilized projectiles. If the aerodynamic forces and moments and the initial conditions are accurately known, an essentially exact simulation of the projectile's synthesized pitching and yawing motion can be readily obtained by numerical methods. A modified trajectory linear theory of the same problem implies an approximate solution.

Approved for public release; distribution unlimited. CL o c m CO I p m m REVIEWED BY

A full six degrees of freedom (6-DOF) flight dynamics model is proposed for the accurate prediction of short and long-range trajectories of small bullets via atmospheric flight to final impact point. The mathematical model is based on the full equations of motion set up in the no-roll body reference frame and is integrated numerically from given initial conditions at the firing site. The projectile maneuvering motion depends on the most significant force and moment variations, in addition to gravity and Magnus effect. The computational flight analysis takes into consideration the Mach number and total angle of attack effects by means of the variable aerodynamic coefficients. For the purposes of the present work, linear interpolation has been applied for aerodynamic coefficients from the official tabulated database. The developed computational method gives satisfactory agreement with published data of verified experiments and computational codes on atmospheric projectile trajectory analysis for various initial firing flight conditions. ___________________________________________________________________________________________ AbstractA full six degrees of freedom (6-DOF) flight dynamics model is proposed for the accurate prediction of short and long-range trajectories of small bullets via atmospheric flight to final impact point. The mathematical model is based on the full equations of motion set up in the no-roll body reference frame and is integrated numerically from given initial conditions at the firing site. The projectile maneuvering motion depends on the most significant force and moment variations, in addition to gravity and Magnus effect. The computational flight analysis takes into consideration the Mach number and total angle of attack effects by means of the variable aerodynamic coefficients. For the purposes of the present work, linear interpolation has been applied for aerodynamic coefficients from the official tabulated database. The developed computational method gives satisfactory agreement with published data of verified experiments and computational codes on atmospheric projectile trajectory analysis for various initial firing flight conditions. ___________________________________________________________________________________________ AbstractA full six degrees of freedom (6-DOF) flight dynamics model is proposed for the accurate prediction of short and long-range trajectories of small bullets via atmospheric flight to final impact point. The mathematical model is based on the full equations of motion set up in the no-roll body reference frame and is integrated numerically from given initial conditions at the firing site. The projectile maneuvering motion depends on the most significant force and moment variations, in addition to gravity and Magnus effect. The computational flight analysis takes into consideration the Mach number and total angle of attack effects by means of the variable aerodynamic coefficients. For the purposes of the present work, linear interpolation has been a...

No abstract