CRYOGENIC PROPELLANT MANAGEMENT - INTEGRATION OF DESIGN, PERFORMANCE AND OPERATIONAL REQUIREMENTS.

Armis L. Worlund, John R. Jamieson, Timothy W. Cole, Tibor I. Lak

Research output: Contribution to journalConference article

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 languageEnglish (US)
Pages (from-to)585-599
Number of pages15
JournalNASA Conference Publication
Issue numberpt 2
StatePublished - Jan 1 1985
Externally publishedYes

Fingerprint

Propellants
Cryogenics
Engines
Vents
Space shuttles
Liquids
Helium
Ice
Stabilization
Hydrogen
Oxygen

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 journalConference article

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