Entry, descent and landing vehicle design space exploration for crewed Mars missions

With the announcement of the Vision for Space Exploration in 2004, NASA has been preparing plans for a crewed mission to Mars in the next few decades. One challenge associated with crewed missions to the Martian surface is the comparatively large mass of planned surface elements which will require an increase of at least an order of magnitude in the landed mass performance of entry, descent and landing (EDL) vehicles compared to previous successful robotic missions and ones currently planned for the near future. The work presented in this thesis attempts to look at the effect of individual vehicle and mission design parameters on the overall EDL system landed mass performance. For this purpose, a planetary EDL simulation and sensitivity analysis tool has been created which allows for the variation of a number of relevant parameters and provides the user with performance data. To date, the tool has been validated with experimental and simulated data for Mars missions. The tool assumes the use of propulsive means for final descent. Using this tool, a number of sensitivity analyses for different parameters for both the entry phase and the entire EDL profile have been conducted. Major insights gleaned from these include the need for research into propulsive descent safety requirements to prevent over-conservatism in establishing the propulsive descent initiation (PDI) altitude since a high PDI altitude can significantly lower EDL vehicle landed mass performance. Another area of research with the potential to provide significant improvements in performance is structural and thermal technology that reduces the aeroshell mass of the vehicle. Finally, the landed mass performance of a reference EDL vehicle with a spherical forebody and a conical aftbody was also evaluated.

Department dc:contributor.department

Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.

Grantor dc:publisher

Massachusetts Institute of Technology

Year dc:date.issued

2008

Author dc:creator

• Khan, Zahra

Advisor dc:contributor.advisor

• Jeffrey Hoffman.

• Aeronautics and Astronautics.

Statement dc:rights

• M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission.

Licence dc:rights.uri

• http://dspace.mit.edu/handle/1721.1/7582

Language dc:language.iso

eng

Handle dc:identifier.uri

http://hdl.handle.net/1721.1/45300

OAI identifier oai:identifier

oai:dspace.mit.edu:1721.1/45300