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The development of a multi-disciplinary CFD code and the application of the code to simulate Titan IV 7-segment solid rocket motor (SRM) transient flowfields, coupled with propellant deformation, are presented. The code consists of four modules and is modularized such that each module can be replaced or updated with the rest of the modules remaining intact. The four modules are: the flow solver, the structural analysis, the thermal analysis, and the grid generation modules. The flow solver module is the core of the code. The salient features of the flow solver are: (a) the boundaries can move in any arbitrary manner, and (h) the conservation principles are always satisfied since the movements of the boundaries and computational grids are incorporated in the equations of motion. Geometrically nonlinear theory of elasticity is used for the structural analysis module. Due to the interactive nature of the code, each simulation can be completed efficiently in a single job submission. Transient phenomena of ignition waves interacting with deformable propellant are presented. The effects of propellant deformation on the pressure distribution inside the motor are discussed.