Simple Control Technology Of The Rocket Projectile Booster Phase Trajectory

With the development of rocket projectiles towards long range and high precision, it is necessary to solve the problem of large dispersion. The simple control technology is a preferred technology to improve the precision of low-cost munitions at present all over the world. The impact dispersion is mainly caused by the dispersion of the direction angle of velocity vectors at the power-off point for rocket projectiles.According to the analysis of the ballistic characteristics during the booster phase for rocket projectiles, a simple control scheme during the booster phase is discussed in this thesis, which is to improve the impact precision. The ballistic parameters are measured during the earlier stage of the booster phase. The impact deviation can be predicted based on the difference between measurements and reference trajectory. Thus the azimuth angle and action times of impulse mortars are to be determined. The attitudes of rocket projectiles are changed due to the action of impulse mortars, through which the simple control scheme is realized.Aiming at the 300mm diameter rocket projectile with low spin speed, the forces and moments acted on the rocket projectile are analyzed in detail. The 6-DOF trajectory model with impulse force and impulse moment is established according to the momentum theorem and angular momentum theorem. The effect of the variation of angle of attack induced by impulse force and impulse moment on the direction angle of velocity at the power-off point is analyzed. The effect of basic parameters and arrangement modes of impulse mortars on the correction efficiency is also analyzed by virtue of simulations. The basic parameters suitable for this type of projectile are selected. A prediction method for estimating the trajectory deviation is developed, according to which the impulse firing strategy is determined. The variation trend of ballistic parameters after impulse action is obtained through simulations under the condition of stable flight. The simulation results indicate that the impulse control scheme proposed in this thesis is feasible.