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Mars Sample Retrieval Lander Thermal Protection System DesignThe Mars Sample Return (MSR) Sample Retrieval Lander (SRL) was slated to launch in 2031 and enter Mars’ atmosphere after a 15-month cruise. After several iterations of vehicle design and trajectories, the latest mission architecture included a 4.72-meter diameter entry capsule entering the Martian atmosphere at 8 km/s, marking a 3.5x increase in kinetic energy when entering the atmosphere in comparison to Mars 2020. Designed to be the heaviest and fastest vehicle to enter Mars’ atmosphere, SRL required slim mass margins, and as such, the thermal protection system (TPS) design methodology needed to be tailored appropriately. The entry capsule aeroshell is composed of a heatshield, backshell, parachute support cone, and parachute lid, as shown in Fig. 1.
Document ID
20260001354
Acquisition Source
Ames Research Center
Document Type
Extended Abstract
Authors
Hannah S Alpert (Ames Research Center Mountain View, United States)
Josh D Monk (Ames Research Center Mountain View, United States)
Milad Mahzari (Ames Research Center Mountain View, United States)
Suman Muppidi (Ames Research Center Mountain View, United States)
Date Acquired
February 12, 2026
Subject Category
Aircraft Design, Testing and Performance
Meeting Information
Meeting: 23rd International Planetary Probe Workshop
Location: Washington, DC
Country: US
Start Date: June 22, 2026
End Date: June 26, 2026
Sponsors: Johns Hopkins University Applied Physics Lab
Funding Number(s)
WBS: 829688.13.06.01.01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Technical Review
NASA Peer Committee

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