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 |
ASJC Scopus subject areas
- Aerospace Engineering
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Worlund, A. L., Jamieson, J. R., Cole, T. W., & Lak, T. I. (1985). CRYOGENIC PROPELLANT MANAGEMENT - INTEGRATION OF DESIGN, PERFORMANCE AND OPERATIONAL REQUIREMENTS. NASA Conference Publication, (pt 2), 585-599.