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Apollo 16 LM-11 descent propulsion system final flight evaluationThe performance of the LM-11 Descent Propulsion System during the Apollo 16 Mission was evaluated and found to be satisfactory. The average engine effective specific impulse was 0.1 second higher than predicted, but well within the predicted 1 sigma uncertainty of 0.2 seconds. The engine performance corrected to standard inlet conditions for the FTP portion of the burn at 50 seconds after ignition was as follows: thrust, 9839 lbf; specific impulse, 306.9 sec; and propellant mixture ratio, 1.592. These values are +0.34, +0.03 and +0.0 percent different, respectively, from the values reported from engine acceptance tests and were within specification limits. Several flight measurement discrepancies that existed during the flight are discussed.
Document ID
19730011138
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Avvenire, A. T.
(TRW Systems Group Redondo Beach, CA, United States)
Date Acquired
September 2, 2013
Publication Date
January 1, 1973
Subject Category
Space Sciences
Report/Patent Number
TRW-20029-H156-R0-00
NASA-CR-128826
Accession Number
73N19865
Funding Number(s)
CONTRACT_GRANT: NAS9-12330
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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