Aerodynamic characteristics and simulation analysis of remote tail control guided projectiles

DOI:	10.11809/bqzbgcxb2023.05.003
Keywords:	guided projectile; aerodynamic characteristics; spinning reduction stern; mechanical model; numerical simulation
Abstract:	Aiming at the problem that the control of a high rotation guided projectile is difficult due to a high rotation speed, this paper designs guided projectile shape by using stern devices for projectile spinning reduction control. The bearing device of the spinning reduction stern is non hard connected with the front cabin, which can ensure that the effect of spinning reduction at the stern can be achieved after the projectile is out of the chamber. Firstly, a physical model of the aerodynamic shape of the projectile is established, and unstructured grid division is done by GAMBIT. Based on the Spalart Allmaras model, the FLUENT software is used to simulate the aerodynamic characteristics of the guided projectile of the spinning reduction stern with non rigid connection. The simulation results show that after 500 iterations, with the increase of Mach number, the convergence value of resistance coefficient increases from 0.174 0 to 0.466 5, the convergence value of lift coefficient increases from 0.066 99 to 0.408 8 , and the convergence value of torque coefficient increases from 0.086 68 to 0.646 0. The pressure on the warhead and the stern increases with the increase of Mach number, and the maximum pressure on the warhead is 9.82e+0.5 Pa and on the tail is 1.71 e+0.5 Pa. The simulation results show that the aerodynamic shape of the guided projectile with an anti spinning stern is reasonable, and the obtained aerodynamic parameters can provide design basis for anti spinning guided projectiles.
Issue:	Vol. 44 No. 5 (2023)
Published:	2023-05-28
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