This paper summarizes a series of computational simulations to protect NASA’s Mars Sample Return spacecraft from meteoroid impact-induced failures, and address the gap between the characteristics of meteoroid fluxes that spacecraft encounter in real-life and those they are exposed to in testing facilities. The study was originally presented at the 17th Hypervelocity Impact Symposium and has been published by the American Society of Mechanical Engineers (ASME). ASME holds the copyright for this paper.