Research on Control Force Aerodynamic Model of a Guided Rocket With an Isolated-rotating Tail Rudder

• DOI: 10.1007/s42405-021-00414-7
• Publication Date: 2021-09-24T16:45:26Z
• Authors: Chen Wang; Libo Ding; He Zhang; Li Xiao; Shihao Zhang
• Keywords: 0103 physical sciences; 01 natural sciences

Isolated rotating tail rudder technology provides a low-cost and miniaturized solution for the correction and guidance of a man-portable rocket. The results of three turbulence models (the Spalart–Allmaras model, standard k–e model, and shear stress transport k–ω model) were compared with wind-tunnel model test data, and the best turbulence model was selected. An aerodynamic model of the rotating tail rudder was developed by identifying its turbulent region, and the influences of the Mach number, angle of attack, and tail rudder speed on the projectile aerodynamics were revealed. The aerodynamic parameters were fitted using a least-squares method, and the vector variation characteristics of the period-averaged control force were analyzed. The results from the shear stress transport k–ω model were closest to the results of the wind-tunnel tests. The aerodynamic model was able to fit the simulation results well. The average control force of the tail rudder over a rotation cycle is not zero, and it increases with increasing angle of attack, Mach number, and tail rudder rotation speed. This study provides a basis for aerodynamic research examining the same type of projectile, and it has guiding significance for the control design of isolated rotating tail rockets.