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In-flight performance of the Viking 75 Orbiter propulsion systemThe configuration of the Viking 75 Spacecraft, which was used in two missions related to the exploration of the planet Mars, is examined and a description of the orbiter propulsion subsystem is provided. The propellants utilized were nitrogen tetroxide and monomethylhydrazine. Gaseous helium was used for pressurization. Orbiter maneuver durations ranged from the 39.4 minute Mars orbit insertion on VO-2, the longest engine firing in space to date, to the 1.7-second station keeping trim on VO-1. Total engine operating time was 2748.2 seconds for VO-1 and 2814.5 seconds for VO-2.
Document ID
19770055729
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Schmit, D. D.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Leeds, M. W.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Vote, F. C.
(California Institute of Technology, Jet Propulsion Laboratory, Pasadena Calif., United States)
Date Acquired
August 9, 2013
Publication Date
July 1, 1977
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 77-894
Meeting Information
Meeting: Propulsion Conference
Location: Orlando, FL
Country: US
Start Date: July 11, 1977
End Date: July 13, 1977
Sponsors: American Institute of Aeronautics and Astronautics, Society of Automotive Engineers
Accession Number
77A38581
Funding Number(s)
CONTRACT_GRANT: NAS7-100
Distribution Limits
Public
Copyright
Other

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