Dimitrios N. Gkritzapis, Elias E. Panagiotopoulos, Dionissios P. Margarisb and Dimitrios G. Papanikas
Abstract: A full six degrees of freedom (6-DOF) simulation flight dynamics model is applied for the accurate prediction of short and long range trajectories of high and low spin-stabilized projectiles and small bullets via atmospheric flight to final impact point. The projectile is assumed to be both rigid (non-flexible), and rotationally symmetric about its spin axis launched at low and high pitch angles. The projectile maneuvering motion depends on the most significant forces and moment variations, in addition to wind and gravity. 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 taking data from official an tabulated database. The aforementioned variable flight model is compared with a trajectory atmospheric motion based on appropriate constant mean values of the aerodynamic projectile coefficients. Static stability, also called gyroscopic stability, is examined as a necessary condition for stable flight motion in order to determine the sufficient initial spinning projectile rotation. The efficiency of the method developed gives satisfactory results compared with published data of verified experiments and computational codes on atmospheric dynamics model flight analysis.
Keywords: Constant and variable aerodynamic coefficients, low and high launched angles, Magnus effects, symmetric projectiles dynamics, stability criteria, trajectory dynamics prediction
Ref: JPyro, Issue 26, 2007, pp3-14
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