A rapid analysis methodology for earth entry vehicle development

Development of an Earth Entry Vehicle and the methodology created to evaluate its structural dynamic response during launch is reported. NASA's future Mars Sample Return Mission requires a robust vehicle to return Martian samples back to Earth for examination. The Earth Entry Vehicle is NASA's solution to this Mars Sample Mission requirement. During launch the vehicle may experience large structural loads. To decrease development time and cost, a parametric and automated finite element analysis methodology has been developed. Models are built using a software coding technique, which allows modification to all aspects of the model including: geometry, material properties, load and boundary conditions, mesh grids, and analysis controls. The methodology allows data to be rapidly generated for a vast array of potential vehicle configurations. Analyses including quasi-static inertial, structure-borne vibration frequency response, and random acoustic analyses are conducted for the parametric analysis. To demonstrate the parametric analysis capability of the methodology, mesh density and cone angle parameters were varied and then all analyses were executed. The analysis methodology is shown to facilitate and expedite future costeffective planetary exploration missions.