Abstract: The work presents rocket launcher jar reduction schema that is fixed on a mechanized vehicle. The matter of stabilizing the rocket launcher is given careful consideration due to extortions resulting from firing of a missile and progressive movement of a vehicle through terrain. An effective firing of a close range, self-targeting rocket missile requires meeting safety standards and few technical requirements. Initial, kinematical flight parameters are elaborated by the missile while still being at the launching pad. The designed flight path that is to be realized by a missile depends upon characteristics of such parameters that are implemented by algorithm of steering. Due to extortions that take place during the flight stage not all of the maneuvers can be realized in practice. Time that is necessary for a missile of a given class to develop the required flight path is very short. In consequence it can lead to an unsuccessful usage of the rocket. Intercepting and targeting process already takes place when the missile is still at the launcher. Nevertheless occurrence of too intensive vibrations can cause surpass allowable parameter values that characterize these processes. Therefore, generated in these way distortions can cause ineffectiveness of a missile already at the take off stage. The elaborated model enables conveying a study of influences of applied regulations on a possibility of reaching the target by missiles fired in turns.
YADDA/CEON