The success of a missile depends directly on its velocity upon motor burnout. This directly translates into missile weight. Saving just ounces can provide significant performance and cost enhancements. The particular area investigated is the Guidance Section Housing or the Shell. The current aluminum 2014-T6 design is used as a baseline for the design requirements and geometric limitations reflected in the composite design. Four materials and four laminate stacking sequence (LSS) families are analyzed to predict the best performer. A final weight savings of 40% is established for a similar normalized strength structure by using the GY70/5208 composite with a LSS of [0₂/± 45/90₂]s.