关键词: 弹丸;垂直发射;姿态调整;直接力控制系统;脉冲推力;内弹道;运动仿真

Abstract: Experimental and numerical studies were carried out respectively to learn about the pitch attitude adjusting process of the projectile which was launched vertically from the ground and controlled by reaction-jet control system （RCS） with different output parameters. Firstly， the impulse lateral thruster， a ground launcher and a synchronous measurement system were designed for the pitch attitude adjusting experiment. A series of tests were conducted in the conditions of different charge weights in the thrusters and various ignition interval time. Based on analysis of the motion pictures captured by high speed cameras， the charge weight and ignition interval time were found to be the two principal factors to determine the final attitude of the projectile and either of them should be selected a proper value for a target attitude angle. Then， an attitude motion computing model of the projectile was established considering the interior ballistic of the thruster. After comparing the results obtained from simulation and test， the prediction error of the model was confirmed to be less than 5%. Subsequently， the variations of the impulse thrust with different charge weights were analyzed according to the computing model. And it was pointed out that the changing rule of the impulse thrust could be affected significantly by the charge weight. Therefore， coupling calculation of the thrust and projectile motion is needed for higher accuracy. In the end， the ignition interval time required for a set of target pitch angles with different charge weights was calculated， which will provide meaningful reference data for further researches.

Key words: Projectile;Vertical launching;Posture adjustment;Reaction-jet control system;Impulse thrust;Interior ballistic;Motion simulation