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Analytical Assessment of the Reciprocating Feed SystemA preliminary analysis tool has been created in Microsoft Excel to determine deliverable payload mass, total system mass, and performance of spacecraft systems using various types of propellant feed systems. These mass estimates are conducted by inserting into the user interface the basic mission parameters (e.g., thrust, burn time, specific impulse, mixture ratio, etc.), system architecture (e.g., propulsion system type and characteristics, propellants, pressurization system type, etc.), and design properties (e.g., material properties, safety factors, etc.). Different propellant feed and pressurization systems are available for comparison in the program. This gives the user the ability to compare conventional pressure fed, reciprocating feed system (RFS), autogenous pressurization thrust augmentation (APTA RFS), and turbopump systems with the deliverable payload, inert mass, and total system mass being the primary comparison metrics. Analyses of several types of missions and spacecraft were conducted and it was found that the RFS offers a performance improvement, especially in terms of delivered payload, over conventional pressure fed systems. Furthermore, it is competitive with a turbopump system at low to moderate chamber pressures, up to approximately 1,500 psi. Various example cases estimating the system mass and deliverable payload of several types of spacecraft are presented that illustrate the potential system performance advantages of the RFS. In addition, a reliability assessment of the RFS was conducted, comparing it to simplified conventional pressure fed and turbopump systems, based on MIL-STD 756B; these results showed that the RFS offers higher reliability, and thus substantially longer periods between system refurbishment, than turbopump systems, and is competitive with conventional pressure fed systems. This is primarily the result of the intrinsic RFS fail-operational capability with three run tanks, since the system can operate with just two run tanks.
Document ID
20060047647
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Eddleman, David E.
(Qualis Corp. Huntsville, AL, United States)
Blackmon, James B.
(Alabama Univ. Huntsville, AL, United States)
Morton, Christopher D.
(Alabama Univ. Huntsville, AL, United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2006
Subject Category
Spacecraft Propulsion And Power
Meeting Information
Meeting: 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
Location: Sacramento, CA
Country: United States
Start Date: July 9, 2006
End Date: July 12, 2006
Sponsors: American Society of Mechanical Engineers, American Inst. of Aeronautics and Astronautics, Society of Automotive Engineers, Inc., American Society for Electrical Engineers
Funding Number(s)
CONTRACT_GRANT: NNM05AA22A
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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