Abstract
The integration of some of the unique design features of the Shuttle elements into a cryogenic propellant management system is described. The implementation and verification of the design/operational changes resulting from design deficiencies and/or element incompatibilities encountered subsequent to the critical design reviews are emphasized. Major topics include subsystem designs to provide liquid oxygen (LO//2) tank pressure stabilization, LO//2 facility vent for ice prevention, liquid hydrogen (LH//2) feedline high point bleed, pogo suppression on the Space Shuttle Main Engine (SSME), LO//2 low level cutoff, Orbiter/engine propellant dump, and LO//2 main feedline helium injection for geyser prevention. (Author abstract. )
| Original language | English (US) |
|---|---|
| Pages (from-to) | 585-599 |
| Number of pages | 15 |
| Journal | NASA Conference Publication |
| Issue number | pt 2 |
| State | Published - Jan 1 1985 |
| Externally published | Yes |
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ASJC Scopus subject areas
- Aerospace Engineering
Cite this
CRYOGENIC PROPELLANT MANAGEMENT - INTEGRATION OF DESIGN, PERFORMANCE AND OPERATIONAL REQUIREMENTS. / Worlund, Armis L.; Jamieson, John R.; Cole, Timothy W.; Lak, Tibor I.
In: NASA Conference Publication, No. pt 2, 01.01.1985, p. 585-599.Research output: Contribution to journal › Conference article
}
TY - JOUR
T1 - CRYOGENIC PROPELLANT MANAGEMENT - INTEGRATION OF DESIGN, PERFORMANCE AND OPERATIONAL REQUIREMENTS.
AU - Worlund, Armis L.
AU - Jamieson, John R.
AU - Cole, Timothy W.
AU - Lak, Tibor I.
PY - 1985/1/1
Y1 - 1985/1/1
N2 - The integration of some of the unique design features of the Shuttle elements into a cryogenic propellant management system is described. The implementation and verification of the design/operational changes resulting from design deficiencies and/or element incompatibilities encountered subsequent to the critical design reviews are emphasized. Major topics include subsystem designs to provide liquid oxygen (LO//2) tank pressure stabilization, LO//2 facility vent for ice prevention, liquid hydrogen (LH//2) feedline high point bleed, pogo suppression on the Space Shuttle Main Engine (SSME), LO//2 low level cutoff, Orbiter/engine propellant dump, and LO//2 main feedline helium injection for geyser prevention. (Author abstract. )
AB - The integration of some of the unique design features of the Shuttle elements into a cryogenic propellant management system is described. The implementation and verification of the design/operational changes resulting from design deficiencies and/or element incompatibilities encountered subsequent to the critical design reviews are emphasized. Major topics include subsystem designs to provide liquid oxygen (LO//2) tank pressure stabilization, LO//2 facility vent for ice prevention, liquid hydrogen (LH//2) feedline high point bleed, pogo suppression on the Space Shuttle Main Engine (SSME), LO//2 low level cutoff, Orbiter/engine propellant dump, and LO//2 main feedline helium injection for geyser prevention. (Author abstract. )
UR - http://www.scopus.com/inward/record.url?scp=0021975521&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=0021975521&partnerID=8YFLogxK
M3 - Conference article
AN - SCOPUS:0021975521
SP - 585
EP - 599
JO - NASA Conference Publication
JF - NASA Conference Publication
SN - 0191-7811
IS - pt 2
ER -