Abstract. The analysis focuses on the dynamics of a hypothetical anti-aircraft system during the missile launch. The results of the computer simulation of motion of the launcher-missile system are represented graphically. The diagrams provide information about the range of kinematic excitations acting on the opto-electro-mechanical coordinator of the target in a self-guided missile.

Abstract. The paper discusses the missile lift-off from a launcher placed on a motor vehicle. The stimulation of the assembly vibration results from the input generated by the road and the missile firing. The unfavourable input generated in the course of assembly operation has an impact on the characteristics of the initial missile flight parameters. The aim of the paper is to apply the hybrid vibroisolation system of the launcher turret in order to improve the conditions of the missile launch from the assembly. The active system reducing the occurring disturbance allows to control the launcher turret vibrations. Owing to that it is possible influence effectively the initial missile flight parameters.Key words: missile, vibration, vibroisolation, initial flight parameters. Denotationsyv,ẏv,ÿv -displacement, velocity and linear acceleration of the turret in the vertical direction, ϑv,θv,θv -displacement, velocity and angular acceleration of the turret in the inclination motion, ϕv,φv,φv -displacement, velocity and angular acceleration of the turret in the tilting motion, ξp1,ξp1,ξp1 -displacement, velocity and linear acceleration of the missile in the motion along the launcher guide, ϕp1,φp1,φp1 -displacement, velocity and angular acceleration of the missile in the motion round the longitudinal axis, rp1(rp1x v , rp1y v , rp1y v ) -vector determining the missile centre of inertia, Vp1(Vp1x v , Vp1y v , Vp1z v ) -vector of the missile linear velocity, Vp1, γp1, χp1 -absolute value and direction angles of the missile linear velocity vector, ωp1(ωp1x p , ωp1y p , ωp1z p ) -missile angular velocity vector, εp1(εp1x p , εp1y p , εp1z p ) -missile angular acceleration vector, Pss1, Mss1 -load generated by the take-off engine, mp1, Ip1x p , Ip1y p , Ip1z p -mass and moment of inertia of the missile, g -acceleration of gravity, l1, l2, l3, l4, l5, l6, l ξ , lη, l ζ -direction cosines.

Abstract. The work considers the effect of the kinematic action resulting from the basic motion of the vehicle on the dynamics of the launcher and the gyroscope acting as the drive of the opto-electro-mechanical target coordinator in a self-guided missile. The problem was analyzed using a hypothetical short-range anti-aircraft system. The simulation results were represented graphically.

A discrete model of an unguided rocket missile launcher installed on a motor vehicle was developed on the basis of a real assembly. The model is simplified to a vertical plane; it has four degrees of freedom and is adapted for a modal analysis. A mathematical model was derived using the variational method on the basis of the assumed physical model. Analytical dependencies in the form of adjoint second order equations taking ordinary derivatives describe the dynamics of the considered system. The equations describing the autonomous motion of the system provided a definition of the generalized eigenvalue problem and the age equation forming the basis of the characteristic values. An analytical form of particular integrals was assumed for equations describing proper vibrations and the amplitude distribution coefficients were calculated. Four forms of proper vibrations of the considered system were obtained on the basis of the determined eigenvectors.

The work analyses the operation of the ZSMU-70 weapon module. The results allowed for the development of several guidelines, aiming to shape the dynamic properties of the WW-4 launcher in order to improve the effectiveness of the ZSMU-70 module. This meant that research was carried out at a military training ground. Unguided NLPR-70 missiles were launched. The launching process was recorded using a Phantom high-speed digital camera. The recorded images were then analysed using TEMA software. Based on the results of empirical research, a physical and mathematical model of the motion was formulated for both the ZSMU-70 module as well as the WW-4 launcher. A computer programme was developed and the motion of the system was simulated during the launching of the missiles. The results of the theoretical analysis were compared with the analogous results from the empirical research. Having the theoretical model verified, some system parameters were changed and guidelines were used to improve the effectiveness of the ZSMU-70 weapon module.