Satellite launch vehicles are assembled either partially or completely in the integration facility and transported to the launch pad using various methods. During transportation, the launch vehicle is subjected to mechanical vibrations caused by the prime mover, ground or rail-induced disturbances, and wind-induced effects. These mechanical vibrations generate dynamic loads, which in turn produce strains and stresses on the structure and components of the launch vehicle. Although the design of the launch vehicle accounts for such loads, it is essential to measure vibration and strain at critical locations. This data is vital to ensure that transportation conditions are normal and that dynamic loads remain within allowable limits. Furthermore, vibration and strain measurements serve as the primary source of information for assessing the severity of any abnormal events that may occur during transportation. This work describes the various sources of vibration that contribute to dynamic loads during the transportation of the launch vehicle from the integration facility to the launch pad via rail. It presents the vibration measurements taken during transportation, the evaluation of dynamic characteristics, and the analysis of measured vibration data across different instances, along with the corresponding results and inferences. The damping characteristics of the launch vehicle under transport conditions in two different directions are also examined. The presence of rigid body modes is discussed, and a comparison is made between the dynamic loads experienced by the launch vehicle and the mobile launch pedestal when transported using two different methods.