Abstract :� � Accuracy of a missile is one of extremely important issues that its designers must be concerned of because it has a direct impact on lives and properties. Therefore, the missile system must be designed very carefully. This is true especially in unguided missiles since the accuracy will depend directly to how azimuth and elevation angles of the launching platform are adjusted. One of the essential factors in the missile launching system is the loading capability of the launching vehicle, including the hydraulic support and vibration isolation equipment without the hydraulic support. Acting loads must be considered as well the strength of the static structure because trust forces from the missile will be present during the launching process in a short period of time causing movement in the structure of the launcher in the form of vibration. And this vibration could impact the accuracy of the missile especially in salvo firing patterns.
This research studies the characteristic of vibration that happen during the launching process by describing it in the form of a mathematical model. The model consists of a spring-damper system in both the front and the rear of the launcher. Vibration is computed at the center of mass in order to study its impact on the specific location. Then the viscous damping in the front and rear are computed in order to find the values. The outcome of the current study can be used to improve the design of the Vehicles