Browse Items (4 total) Browse All Browse by Tag Search Items Subject is exactly "Liquid oxygen" Sort by: TitleCreatorIdentifierDate Added "A Helium Face Seal Application In a Liquid Oxygen Pump." Cieslik, Walter 1969-05-09 "Development of LOX/RP-1 Engines for Saturn/Apollo Launch Vehicles." Bostwick, Leonard C. 1968-06-14 Development of LOX/RP-1 engines for Saturn/Apollo launch vehicles. Bostwick, Leonard C. 1968-06-14 "Development of the Saturn S-IV and S-IVB Liquid Hydrogen Tank Internal Insulation." Dearing, D. L. 1965-08-23 Output Formats atom, csv, dc-rdf, dcmes-xml, json, omeka-xml, rss2 Refine search Identifier Select...devloxrp1eng.pdfdevloxrp1engsatapollaunveh_041107135046.pdfdevofthesatsIVandsIVBliqhydtanintins.pdfspc_stnv_000054spc_stnv_000242spc_stnv_000243spc_stnv_000244 Title Select..."A Helium Face Seal Application In a Liquid Oxygen Pump.""Development of LOX/RP-1 Engines for Saturn/Apollo Launch Vehicles.""Development of the Saturn S-IV and S-IVB Liquid Hydrogen Tank Internal Insulation."Development of LOX/RP-1 engines for Saturn/Apollo launch vehicles. Alternative Title Select...AIAA Paper No. 68-569Douglas Engineering Paper No. 3511FICFS Preprint 24 Description Select...In April of 1960 the Douglas Aircraft Company was awarded a contract to develop the second and uppermost stage for the Saturn I space booster. In order to realize the high specific impulse available, this stage, called the S-IV, was to utilize liquid hydrogen and liquid oxygen as the propellants. After burn-out of the first stage, the S-IV Stage was to ignite its engines at an altitude of approximately 200,000 feet, burn for approximately 8 minutes, and inject a 20,000 lb spacecraft into a low earth orbit. This program represented Douglas's first major endeavor with liquid hydrogen. It was necessary to develop an insulation for the S-IV Stage that was capable of withstanding the thermal shock associated with loading, could provide adequate insulative properties to limit the flow of heat into the hydrogen, and was of minimum weight. This latter fact cannot be over emphasized because every extra pound of insulation is one less pound of available payload weight.Presented at the Fourth International Conference on Fluid Sealing held in conjunction with the 24th annual meeting in Philadelphia, May 5-9, 1969.The development of liquid rocket engines follow similar patterns regardless of engine size. During the development of the H-1 and F-1 engines, many problems were encountered. Methods of solving the combustion instability problem are discussed. A description is given of the major components of each engine, outlining their unique features. The requirements for an insulation cocoon are discussed. Problems associated with materials substitution are provided; also highlighted is the fact that problems occur after engine deliveries and require continued development support. Safety features incorporated on the engines are mentioned. Solution to problems encountered in flight are discussed. Upratings of both engines systems are presented graphically.; On the NASA Technical Reports Server (NTRS) unclassified. Can also be found on AIAA.The development of liquid rocket engines follow similar patterns regardless of engine size. During the development of the H-1 and F-1 engines, may problems were encountered. Mehtods of solving the combustion instability problem are discussed.; AIAA 4th Propulsion Joint Specialist Conference, Cleveland, Ohio, June 10-14, 1968.; Also available on NASA Technical Reports Server (NTRS) as unclassified. Can be ordered. Also on AIAA. Creator Select...American Society of Lubrication EngineersBostwick, Leonard C.Cieslik, WalterDearing, D. L.George C. Marshall Space Flight Center. Test LaboratoryNorth American Aviation. Space and Information Systems Division Temporal Coverage Select...1960-1969 Subject Remove filter...Liquid oxygen Type Select...EssaysReportsText Language Select...en