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Design Enhancement and Improved Post-Actuation Test Method for a 1/4 inch Normally Closed Pyro Valve

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dc.contributor.author Held, T. D. en_US
dc.contributor.author Sweet, C. A. en_US
dc.contributor.author Mantha, K. en_US
dc.date.accessioned 2004-09-30T22:23:52Z
dc.date.available 2004-09-30T22:23:52Z
dc.date.issued 1996-07-01 en_US
dc.identifier.citation Lake Beuna Vista, Florida, USA en_US
dc.identifier.clearanceno 96-1046 en_US
dc.identifier.uri http://hdl.handle.net/2014/26033
dc.description.abstract The NASA/JPL Cassini mission to Saturn will launch in October, 1997 and arrive at Saturn in the year 2004 with a 4 year mission to orbit the planet. The main propulsion thrust vector and attitude control for the spacecraft is supplied by the Cassini Propulsion Module Subsystem (C-PMS). This system will use numerous ordnance-actuated, normally-closed (NC) pyro valves to perform mission critical tasks over the 11 year mean mission duration (NMD). The proper operation of this NC valve requires it to isolate fluid flow until commanded open. Once open, the valve must allow an unobstructed flow path and seal internally to prevent leakage external to the valve. This paper documents a design evolution to a qualified, Viking heritage design with improvements in design details that control external leakage to levels that support the planetary mission of this spacecraft. In addition, it addresses an improved post-actuation leak test technique, used to better detect gas leakage past the valve's primary metal-to-metal internal seal. en_US
dc.format.extent 382137 bytes
dc.format.mimetype application/pdf
dc.language.iso en_US
dc.subject.other Cassini NC valve Cassini Propulsion Module Subsystem C-PMS pyro valves NC pyro valves en_US
dc.title Design Enhancement and Improved Post-Actuation Test Method for a 1/4 inch Normally Closed Pyro Valve en_US


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