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A simulation study of emergency lunar escape to orbit using several simplified manual guidance and control techniquesA fixed-base piloted simulator investigation has been made of the feasibility of using any of several manual guidance and control techniques for emergency lunar escape to orbit with very simplified, lightweight vehicle systems. The escape-to-orbit vehicles accommodate two men, but one man performs all of the guidance and control functions. Three basic attitude-control modes and four manually executed trajectory-guidance schemes were used successfully during approximately 125 simulated flights under a variety of conditions. These conditions included thrust misalinement, uneven propellant drain, and a vehicle moment-of-inertia range of 250 to 12,000 slugs per square foot. Two types of results are presented - orbit characteristics and pilot ratings of vehicle handling qualities.
Document ID
19720003294
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Middleton, D. B. (NASA Langley Research Center Hampton, VA, United States)
Hurt, G. J., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
October 1, 1971
Subject Category
Space Vehicles
Report/Patent Number
L-7836
NASA-TN-D-6488
Accession Number
72N10943
Funding Number(s)
PROJECT: RTOP 970-33-10-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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