NDLI: Low-thrust chemical propulsion system propellant expulsion and thermal conditioning study

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Low-thrust chemical propulsion system propellant expulsion and thermal conditioning study

Content Provider	NASA Technical Reports Server (NTRS)
Author	Hill, M. Merino, F. Wakabayashi, I. Pleasant, R. L.
Copyright Year	1982
Description	Thermal conditioning systems for satisfying engine net positive suction pressure (NPSP) requirements, and propellant expulsion systems for achieving propellant dump during a return-to-launch site (RTLS) abort were studied for LH2/LO2 and LCH4/LO2 upper stage propellant combinations. A state-of-the-art thermal conditioning system employing helium injection beneath the liquid surface shows the lowest weight penalty for LO2 and LCH4. A technology system incorporating a thermal subcooler (heat exchanger) for engine NPSP results in the lowest weight penalty for the LH2 tank. A preliminary design of two state-of-the-art and two new technology systems indicates a weight penalty difference too small to warrant development of a LH2 thermal subcooler. Analysis results showed that the LH2/LO2 propellant expulsion system is optimized for maximum dump line diameters, whereas the LCH4/LO2 system is optimized for minimum dump line diameter (LCH4) and maximum dump line diameter (LO2). The primary uncertainty is the accurate determination of two-phase flow rates through the dump system; experimentation is not recommended because this uncertainty is not considered significant.
File Size	6992929
Page Count	218
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19820016412
Archival Resource Key	ark:/13960/t9k40mn1c
Language	English
Publisher Date	1982-04-01
Access Restriction	Open
Subject Keyword	Spacecraft Propulsion And Power Thermodynamics Low Thrust Propulsion Fuel Tank Pressurization Rocket Thrust Venting Heat Exchangers Propellant Tanks Expulsion Heat Transfer Pressure Regulators Chemical Propulsion Spacecraft Propulsion Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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