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Liquid fluorine/hydrazine rhenium thruster updateThe status of a fluorine/hydrazine thruster development program is discussed. A solid rhenium metal sea-level thrust chamber was successfully fabricated and tested for a total run duration of 1075 s with 17 starts. Rhenium fabrication methods are discussed. A test program was conducted to evaluate performance and chamber cooling. Acceptable performance was reached and cooling was adequate. A flight-type injector was fabricated that achieved an average extrapolated performance value of 3608 N-s/kg (368 lbf-s/lbm). Altitude thrust chambers were fabricated. One chamber incorporates a rhenium combustor and nozzle with an area ratio of 15:1, and a columbium nozzle extension with area ratios from 15:1 to 60:1. The other chamber was fabricated completely with a carbon/carbon composite. Because of the attributes of rhenium for use in high-temperature applications, a program to provide the materials and processes technology needed to reliably fabricate and/or repair vapor-deposited rhenium parts of relatively large size and complex shape is recommended.
Document ID
19830026748
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Appel, M. A.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Kaplan, R. B.
(Ultramet Co.)
Tuffias, R. H.
(Ultramet Co.)
Date Acquired
August 11, 2013
Publication Date
February 1, 1983
Publication Information
Publication: APL The 1983 JANNAF Propulsion Meeting, Vol. 1
Subject Category
Spacecraft Propulsion And Power
Accession Number
83N35019
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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