Mars Ascent Vehicle system studies and baseline conceptual design

Abstract

The Mars Ascent Vehicle (MAV) is a critical mission element of the Mars Sample Return campaign that delivers the Martian sample from Mars surface to orbit for rendezvous with retrieving spacecraft and sample return to earth. The MAV design presents significant challenges in that it must fit in the Lander mission architecture, have a minimized total system mass (MAV and igloo/erector support system) with a mass goal of less than 360 kg, and deliver the 5 kg Martian sample payload to a 460 to 580km orbit. The MAV must also withstand the harsh Mars thermal environment for up to 9 months where power consumption for thermal conditioning and operation further impacts the mass allocation to the MAV. Northrop Grumman Aerospace Systems, in collaboration with NASA GRC and JPL, conducted a MAV system study and component definition under a National Research Announcement, NASA In-Space Propulsion program. The study investigated a two-stage liquid propulsion concept, an optimized MAV trajectory, guidance, navigation, and control, thermal requirements, MAV components, and MAV support systems. The results of the study and baseline MAV system design are presented in this report.