Structural Concept Study for Planetary Probes and Sample Return Vehicles

Abstract

A parametric structural investigation of a new atmospheric entry vehicle concept for future planetary probes and sample return vehicles was conducted. During launch and reentry, the vehicle may experience large structural loads. To enable rapid assessment of candidate vehicle configurations for different missions, a parametric structural dynamics analysis methodology was developed. The methodology generates finite-element models and enables rapid modification to all aspects of the models, including geometry, material properties, load and boundary conditions, mesh parameters, and analysis controls. Analyses including quasi-static inertial loading, vibration frequency response, acoustic loading, and reentry loading were conducted for the structural concept study. Several geometry, mass, and material parameters were varied from to of their baseline value and analyzed. A total of 136 analyses were conducted on 34 unique vehicle configurations. Of the parameters investigated, cone angle and vehicle diameter were found to be the most influential on the vehicle’s mass and structural response. The highest stress observed was for an inertial launch analysis conducted on a cone angle model, which had 2.7x the baseline stress and only 1.4x the baseline mass. This analysis methodology is shown to facilitate and expedite future planetary exploration mission analyses.