Abstract This thesis presents an investigation of factors leading to the Challenger Space Shuttle disaster. It presents a Finite Element investigation of the effect temperature has on the ability of O-Rings to seal, and how this relates to the contributing management process factors in the Challenger Space Shuttle disaster. The deformation vs temperature of a VITON rubber O-Ring, is analysed under conditions from NASA technical papers to accurately model the O-Rings in the Challenger disaster. Deformation was measured across a temperature range of 22 0C to -140C covering the range from the typical Florida ambient temperature to the recorded temperature of the booster joint at the time of launch. The results conclude that the ability of O-rings to seal decreases with temperature as they become less able to deform. The results presented in this thesis represent the data that was required by engineers to stop the original launch. This thesis also analyses new processes now in place at NASA and how such processes help to avoid tragic disasters like Challenger from occurring again by following a proper decision making process.