Modeling and Finite Element Analysis of the Combustion Chamber in the Motor Mount of the First Stage of a Missile

In the present work the combustion chamber of the first stage of a missile has been modeled, which is cylindrical in shape. The cylindrical combustion chamber has been modeled inside the motor mount composed of graphite fiber in epoxy matrix with multi-directional fiber orientation. In the present analysis three types of materials, namely, titanium alloy, laminated composites with fiber orientations [0º/ ± 45º/90º]s and [0º/ ± 30º/ ± 45º/90º]s have been considered for finite element modeling and analysis of combustion chamber of a missile. A structural analysis of the combustion chamber has been conducted for the three types of materials to evaluate its performance under operating conditions involving total deformation and hoop stress. This generated stresses due to mechanical loads have been analyzed to verify the maximum limit that can be withstand by the specified materials. This step is essential for validating the design of the cylindrical chamber can withstand the combined effects of mechanical loads and operational conditions without failure. It has been found from the finite element analysis that the stress produced due to mechanical load is highest in the titanium alloy and least in the composite with fiber orientation [0º/ ± 30º/ ± 45º/90º]s, showing the least deformation in the composite with fiber orientation [0º/ ± 30º/ ± 45º/90º]s, followed by the composite with fiber orientation [0º/ ± 45º/90º]s and showing the highest deformation in the titanium alloy. Therefore, it could be concluded that the composite with fiber orientation [0º/ ± 30º/ ± 45º/90º]s is suitable material for missile combustion chamber.