تحليل ارتعاشات و پايداري ديناميكي يك موشك بالستيك سوخت مايع تحت تاثير تلاطم سوخت

In this paper, the governing equations of motion for a liquid fuel rigid ballistic missile, by considering the fuel sloshing effect are derived. The missile performs under a guidance law control system. The external forces are due to aerodynamic and thrust forces and the sloshing effect in the linear range is modeled as simple mass-springdamper system. In order to solve the equations of motion, in each time step, one needs to compute the motion variables for the missile dry- structure and the sloshing degree of freedom. Finally, the solution is obtained and the simulation results are presented in such a way that in each step motion variables of dry-structure and sloshing modes are calculated.