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Ares V Utilization in Support of a Human Mission to Mars
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Author and Affiliation:
Holladay, J. B.(NASA Marshall Space Flight Center, Huntsville, AL, United States);
Jaap, J. P.(NASA Marshall Space Flight Center, Huntsville, AL, United States);
Pinson, R. M.(NASA Marshall Space Flight Center, Huntsville, AL, United States);
Creech, S. D.(NASA Marshall Space Flight Center, Huntsville, AL, United States);
Ryan, R. M.(NASA Marshall Space Flight Center, Huntsville, AL, United States);
Monk, T. S.(Zero Point Frontiers Corp., Huntsville, AL, United States);
Baggett. K. E.(Zero Point Frontiers Corp., Huntsville, AL, United States);
Runager, M. D.(Jacobs Technologies Engineering Science Contract Group, Huntsville, AL, United States);
Dux, I. J.(NASA Glenn Research Center, Cleveland, OH, United States);
Hack, K. J.(NASA Glenn Research Center, Cleveland, OH, United States);
Hopkins, J. M.(NASA Kennedy Space Center, Cocoa Beach, FL, United States);
Brown, C. E.(NASA Kennedy Space Center, Cocoa Beach, FL, United States);
Manning, T. A.(NASA Ames Research Center, Moffett Field, CA, United States)
Abstract: During the analysis cycles of Phase A-Cycle 3 (PA-C3) and the follow-on 8-wk minicycle of PA-C3', the Ares V team assessed the Ares V PA-C3D configuration to the Mars Design Reference Mission as defined in the Constellation Architecture Requirements Document and further described in Mars Design Reference Architecture 5.0 (DRA 5.0) that was publicly released in July 2009. The ability to support the reference approach for the crewed Mars mission was confirmed through this analysis (7-launch nuclear thermal propulsion (NTP) architecture) and the reference chemical approach as defined in DRA 5.0 (11- or 12-launch chemical propulsion module approach). Additional chemical propulsion options were defined that utilized additional technology investments (primarily in-space cryogenic propellant transfer) that allowed for the same mission to be accomplished with 9 launches rather than the 11 or 12, as documented in DRA 5.0 and associated follow-on activities. This nine-launch chemical propulsion approach showed a unique ability to decouple the architecture from major technological developments (such as zero-boiloff technology or the development of NTP stages) and allowed for a relaxing of the infrastructure investments required to support a very rapid launch rate (30-day launch spacing as documented in DRA 5.0). As an enhancing capability, it also shows promise in allowing for and incorporating the development of a commercial market for cryogenic propellant delivery on orbit, without placing such development on the critical path of beyond low-Earth orbit exploration. The ability of Ares V to support all of the aforementioned options and discussion of key forward work that is required to fully understand the complexities and challenges presented by the Mars mission is further documented herein.
Publication Date: Nov 01, 2010
Document ID:
20100042324
(Acquired Dec 21, 2010)
Subject Category: LAUNCH VEHICLES AND LAUNCH OPERATIONS
Report/Patent Number: NASA/TM-2010-216450, M-1299
Document Type: Technical Report
Financial Sponsor: NASA Marshall Space Flight Center; Huntsville, AL, United States
Organization Source: NASA Marshall Space Flight Center; Huntsville, AL, United States
Description: 94p; In English; Original contains color illustrations
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright; Distribution as joint owner in the copyright
NASA Terms: ARES 5 CARGO LAUNCH VEHICLE; MARS MISSIONS; CHEMICAL PROPULSION; LAUNCHING; NUCLEAR PROPULSION; CRYOGENICS; LOW EARTH ORBITS; PROPELLANT TRANSFER; CYCLES
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