Development of the Saturn S-IV and S-IVB LIQUID hydrogen tank internal insulation.
Saturn S-IV and S-IVB liquid hydrogen tank internal insulation, using polyurethane foam reinforced with fiberglass threads
INSULATOR↗
SEARCH · Search NASA
Results for “SATURN S-4 STAGE”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Saturn s-iv cryogenic weigh system. i - propellant utilization.
Cryogenic weigh system for calibrating propellant masses for Saturn S-IV stage
SATURN S-4 STAGE↗
The Saturn S-IV stage base thermal environment flight and scale model data comparison.
Base heating in Saturn S-IV stage from exhaust reversal, comparing flight and scale model data
BASE HEATING↗
Design of cryogenic fluid systems in the S-IV STAGE propulsion system.
Reliability design concepts in cryogenic fluid systems in Saturn S-IV stage propulsion system, noting hydrogen and LOX tank pressurization systems
SATURN S-4 STAGE↗
Saturn s-iv cryogenic weigh system. ii - weigh operations.
Cryogenic calibration weigh system using electronic transducers and measuring apparatus for Saturn S-IV propellant mass determination
MEASURING APPARATUS↗
Saturn s-iv cryogenic weigh system. iv - safety.
Hydrogen and oxygen detectors for safety measures in Saturn S-IV cryogenic weigh system
SATURN S-4 STAGE↗
Saturn base heating handbook
A handbook containing a summary of model and flight test base heating data from the S-1, S-1B, S-4, S-1C, and S-2 stages is presented. A review of the available prediction methods is included. Experimental data are provided to make the handbook a single source of Saturn base heating data which can be used for preliminary base heating design predictions of launch vehicles.
Mullen, C. R.↗
Mission Planning for Pioneer Saturn/Uranus Atmospheric Probe Missions
Mission planning for a series of atmospheric probe missions to Saturn and Uranus using a modified Pioneer spacecraft launched in 1979 and 1980 was examined. The operational options and the associated systems requirements consistent with the major scientific goals and spacecraft constraints of the missions is summarized. It is feasible to obtain in-situ atmospheric measurements in the atmosphere of Saturn and Uranus down to a pressure level of 10 bars using a common probe and spacecraft design. Spacecraft can be launched to both objectives with an adequate launch window in 1979 and 1980 using a Titan/Centaur launch vehicle with a TE-364-4 upper stage. Other scientific objectives can be accomplished by the flyby spacecraft. Encounters with the satellite Titan and RF occultations of Saturn, the ring system of Saturn, and Uranus can be obtained.
Swenson, B. L.↗
Risk Assessment for Titanium Pressure Vessels Operating Inside the ARES I's Liquid Hydrogen Tank Environment
Titanium alloy (Ti-6-4) is currently being proposed for the manufacturing of pressure vessels (PV) for storage of compressed helium gas, which are mounted inside the ARES I's liquid hydrogen (LH2) tank. At cryogenic temperature, titanium alloys usually have the highest strength-to-weight ratio property and have been considered as the metallic materials of choice for lightweight PV operating in LH2 environment. Titanium PV s are also considered as heritage hardware because they have been used by NASA for the Saturn IV-B rocket s LH2 tank in the mid 1960 s. However, hydrogen embrittlement is possible if Ti-6-4 alloy is exposed to gaseous hydrogen at certain pressure and temperature during the LH2 tank filling and draining operations on the launch pad, and during the J2X engine burn period for the ARES I s upper stage. Additionally, the fracture toughness and ductility properties of Ti-6-4 are significantly decreased at cryogenic temperature. These factors do not necessary preclude the use of titanium PV in hydrogen or at cryogenic applications; however, their synergistic effects and the material damage tolerance must be accounted for in the mission life assessment for PV s, which are considered as fracture critical hardware. In this paper, an overview of the risk assessment for Ti-6-4 alloy, strategy to control hydrogen embrittlement and brief metallic material trade study for PV operating in LH2 tank will be presented.
Lee, Jonathan A.↗
Mission requirements: Skylab rescue mission SL-R
The Skylab Program includes three low earth orbit missions. These missions are designated SL-1/SL-2,SL-3 and SL-4. In addition to the three nominal Skylab missions, the program includes the Skylab Rescue Mission (SL-R). The SL-R mission is designed to provide a safe return of the Skylab crew in the event the Command Service Module (CSM) becomes disabled while docked to the Saturn Workshop (SWS). Mission requirements for the SL-R mission only are presented. SL-R mission configuration will be a CSM (modified with a field installed kit) manned by two crewmen launched on a Saturn IB Launch Vechicle. The SL-R CSM will rendezvous and dock with the SWS (or Orbital Assembly (OA), consisting of the SWS and disabled CSM, if the disabled CSM has not previously been jettisoned). The SWS configuration includes a Multiple Docking Adapter (MDA), Apollo Telescope Mount (ATM), Airlock Module (AM), and an S-IVB stage (modified as an Orbital Workshop (OWS), previously launched and inserted into orbit on a two-stage Saturn V Launch Vehicle for the SL-1/SL-2 mission.
Source record↗