Finite element analysis of vehicle-structure interactions during launching of remotely piloted air-vehicles

The problem of finite element modeling and analysis of dynamic interactions between the launcher and a remotely piloted aircraft structure is considered. The governing equations of motion are shown to constitute a set of ordinary differential equations with time varying structural matrices. An iterative strategy that treats separately the dynamics of the launcher and the aircraft is developed. The strategy is shown to be capable of including the effects of several other sources of dynamic excitations such as guideway unevenness, rocket thrust, running motor, and transients during the initial release and final take-off of the aircraft. The usefulness of the analysis in delineating the relative importance of contributions from various sources of excitations is demonstrated.