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Minimum impulse thruster valve design and developmentThe design and development of a minimum impulse thruster valve was conducted, by Moog, under contract by NASA's Jet Propulsion Laboratory, California Institute of Technology, for deep space propulsion systems. The effort was focused on applying known solenoid design techniques scaled to provide a 1 -millisecond response capability for monopropellant, hydrazine ACS thruster applications. The valve has an extended operating temperature range of 20(deg)F to +350(deg)F with a total mass of less than 25 grams and nominal power draw of 7 watts. The design solution resulted in providing a solenoid valve that is one-tenth the scale of the standard product line. The valve has the capability of providing a mass flow rate of 0.0009 pounds per second hydrazine. The design life of 1,000,000 cycles was demonstrated both dry and wet. Not all design factors scaled as expected and proved to be the focus of the final development effort. These included the surface interactions, hydrodynamics and driver electronics. The resulting solution applied matured design approaches to minimize the program risk with innovative methods to address the impacts of scale.
Document ID
20060043626
Acquisition Source
Jet Propulsion Laboratory
Document Type
Conference Paper
External Source(s)
Authors
Huftalen, Richard L.
Platt, Andrea L.
Parker, Morgan J.
Yankura, George A.
Date Acquired
August 23, 2013
Publication Date
July 20, 2003
Subject Category
Spacecraft Propulsion And Power
Meeting Information
Meeting: AIAA Joint Propulsion Conference and Exhibit
Location: Huntsville, AL
Country: United States
Start Date: July 20, 2003
End Date: July 23, 2003
Distribution Limits
Public
Copyright
Other
Keywords
impulse thruster valve

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