In order to increase the density of guided rockets, a passive control method was proposed to reduce the trajectory dispersion caused by initial disturbances, thrust misalignment, vertical wind, etc. at the end of boost phase. The basic principle of passive control method was introduced briefly, and then the disturbance motion equations for the rocket projectile were established. The effective conditions to implement passive control on guided rockets were put forward. A technical scheme of installing elastic sabots on rocket projectile was proposed to realize passive control and a simulation was conducted. The simulation results indicate that the passive control scheme can effectively decrease the velocity direction deviation caused by various disturbances factors at the end of boost phase.

To establish more accurate and effective gun dynamics model, which considered fully the coupling influence of projectile and flexible barrel, by introducing the virtual substance into the barrel system, a modeling method for self-propelled guns was presented. Taking a tracked self-propelled gun for an example, combining Ansys and Recurdyn, a multi-body dynamics model was built up. The correlation curves between the experimental data and the simulation result under the same firing conditions were obtained. The results show that the model can describe accurately the dynamic response and the projectile movement, which can provide theoretical references for the further research on gun launch dynamics characteristics.

An effective method of trajectory reconstruction is presented in order to identify aerodynamic parameters. A novel smoother URTSS, which can get more optimal ballistic parameters, is introduced because of the biggish error caused by the uncertain initial conditions. Finally the validity of the method is verified by the experimental data. It also proves that URTSS can improves the accuracy of the identification of aerodynamic parameters.

The initial velocity of a projectile has great effects on the weapon performances and it influences firing accuracy. It is meaningful to know the motion of projectiles in after-effect period. This article studies the motion of the projectile by using a Six Degrees-of-Freedom rigid model and chimera method, which is suitble to simulate large-scale deplacemengt of projectiles. The results of the simulation show that the velocity of the projectile increases rapidly first and decreases slowly after reaching the peak value.

In order to improve the guidance accuracy of long-range rockets, a GPS/INS integrated navigation method with combination of position, velocity and attitude was applied. The GPS/INS integrated navigation system taking the position and velocity from INS and attitude from GPS as observables was studied. The error model of system was established and the Kalman filter was designed. A 6-DOF trajectory simulation was put forward and the correction capability of the INS measurement error by using GPS attitude measurement information was analyzed. The simulation results verify the feasibility and effectiveness of the integrated navigation method.