Missile Launch-Induced Dynamics of a Vehicle-Integrated Air Defense System

Integration of missile launch capabilities into mobile ground platforms introduces significant engineering challenges, particularly in maintaining structural integrity under nonlinear transient dynamics induced by high-impulse loading. Previous studies have primarily addressed fixed or heavy launch platforms, comparatively fewer have examined high mobility vehicle-integrated air defense systems nonlinear coupling. The development of simulation environment replicating real-world launch conditions remains an active area of investigation in context of military personnel training, especially as platforms undergo rapid modernization and next-generation weapons systems are introduced. This study proposes a nonlinear computational framework to simulate launch-induced dynamic response of an air defense system mounted on a high mobility multipurpose wheeled vehicle (HMMWV). A five degree-of-freedom model was developed using Lagrangian mechanics. The second-order differential equations of the model were numerically solved using the fourth order Runge-Kutta method. Simulations were performed at three launcher pitch angles (30°, 45°, and 60°) enabling high-resolution analysis of recoil-induced oscillations, impulse propagation and system stabilization times. The results reveal interaction between propulsion-generated excitation force and chassis performance, which is significantly influenced by geometrical parameters of chassis components. The validated modelling framework offers application for improved mobile air defense systems performance and simulation-based training environments and future system integration studies.