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Crew Exploration Vehicle Ascent Abort Trajectory Analysis and OptimizationThe Orion Crew Exploration Vehicle is the first crewed capsule design to be developed by NASA since Project Apollo. Unlike Apollo, however, the CEV is being designed for service in both Lunar and International Space Station missions. Ascent aborts pose some issues that were not present for Apollo, due to its launch azimuth, nor Space Shuttle, due to its cross range capability. The requirement that a North Atlantic splashdown following an abort be avoidable, in conjunction with the requirement for overlapping abort modes to maximize crew survivability, drives the thrust level of the service module main engine. This paper summarizes 3DOF analysis conducted by NASA to aid in the determination of the appropriate propulsion system for the service module, and the appropriate propellant loading for ISS missions such that crew survivability is maximized.
Document ID
20080006650
Acquisition Source
Glenn Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Falck, Robert D.
(NASA Glenn Research Center Cleveland, OH, United States)
Gefert, Leon P.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
August 24, 2013
Publication Date
December 1, 2007
Subject Category
Launch Vehicles And Launch Operations
Report/Patent Number
NASA/TM-2007-214996
AIAA Paper-2007-6775
E-16199
Meeting Information
Meeting: AIAA Guidance, Navigation and Control Conference and Exhibit
Location: Hilton Head, SC
Country: United States
Start Date: August 20, 2007
End Date: August 23, 2007
Funding Number(s)
WBS: WBS 644423.06.32.03.15.03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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