The reliability contribution of the pilot to a large launch vehicle control system.
Reliability contribution of pilot using manual backup control for first stage of Saturn V tested using simulation
MANUAL CONTROL↗
SEARCH · Search NASA
Results for “SATURN V LAUNCH VEHICLE”
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.
Head to head test procedures for the hydrodynamic support of Saturn V
Test procedures for functional tests of hydrodynamic supports for Saturn V vehicle
GROUND SUPPORT SYSTEM↗
Static aerodynamic characteristics of the aborted Apollo-Saturn V vehicle
Static aerodynamic characteristics of aborted Apollo-Saturn V vehicle
APOLLO SPACECRAFT↗
Apollo/Saturn V launch operations.
Integration, testing and launching of flight hardware for Apollo/Saturn V space vehicle at Kennedy Space Center
LAUNCHING FACILITY↗
Launching facilities for space vehicles
Launching facilities for space rockets including buildings, assembly and test program and platforms for Saturn V Moon shot
SATURN V LAUNCH VEHICLE↗
A lunar landing guidance system for soft- precision landings.
Guidance system for accurate soft lunar landing including error sensitivities evaluation and applications to Saturn V Lunar Logistic Vehicle
SATURN V LAUNCH VEHICLE↗
Launch vehicles for the Apollo program.
Structural, propulsion, guidance and flight control systems of Saturn IB and V Apollo launch vehicles
SATURN LAUNCH VEHICLE↗
Development of weld fabrication techniques for the s-ic saturn v vehicle.
Material selection, vertical assembly with soft tooling and equipment evaluation in weld fabrication techniques for s-1c booster stage of saturn v vehicle
SPACECRAFT CONSTRUCTION MATERIAL↗
Powered flight trajectory determination techniques as applied to Saturn V vehicles.
Powered flight trajectory determination for Saturn V vehicles through computer method
SPACECRAFT TRAJECTORY↗
Sat V growth and flexibility.
Uprated Saturn V vehicles and intermediate payload Saturn vehicles, studying costs, flexibility, performance and boost-assist components
SATURN V LAUNCH VEHICLE↗
Challenge of the century
Development of reusable, improved space vehicles for future space exploration
SPACE EXPLORATION↗
Development of a lightweight external insulation system for liquid-hydrogen stages of the saturn v vehicle.
Lightweight external insulation system for liquid hydrogen stages of Saturn V vehicle
CRYOGENIC STORAGE↗
Techniques for the remote monitoring of hypergolic propellant leaks
Detection of vehicle ground support equipment malfunctions, especially hypergolic propellant leakage, for safety of personnel and hardware
LEAKAGE↗
A study of electronic packages environmental control systems and vehicle thermal systems integration Quarterly report no. 1, May - Jul. 1966
Environmental control systems for thermally conditioning individual electronic packages for Saturn space missions
SATURN V LAUNCH VEHICLE↗
Free flight simulated on ground with the Apollo Saturn V space vehicle.
Hydraulic support system for free flight simulation with Saturn V-Apollo vehicle, discussing stability requirements, upper bounds of system design, conversion from nonlinear to linear model, etc
VIBRATION TESTING↗
A hydraulic support for free-flight simulation with the Saturn-V Apollo vehicle.
Hydraulic support system for free-flight simulation with Saturn V-Apollo vehicle, discussing stability requirements, upper bounds of system design, conversion from nonlinear to linear model, etc
HYDRAULIC SYSTEM↗
A Modular Nuclear Vehicle System with Multi-Mission Capability for Mars Stopover Missions
In depth studies conducted over the past two years have established a modular nuclear stage concept which offers multi-mission capability with a maximum of hardware commonality, i.e., a concept which minimizes total hardware development effort and investment in facilities while providing a logical development evolution from ground test systems to flight test and from initial to more ambitious space applications. Recent results oriented toward the definition and application of such a vehicle concept for the manned Mars landing mission are presented. The basic modular concept employing NERVA nuclear rocket engines is reviewed and the mission peculiar factors affecting the module sizes and number of modules required are discussed. Specific results presented are restricted primarily to the 1982 Mars landing mission via the opposition class mission mode since this is the earliest anticipated date for such a mission. The realistic effects of orbital launch windows are considered and brief discussions of orbital assembly and packaging options with a modular approach are given. Typical ground launch and orbital assembly operations are defined assuming an uprated Saturn V class launch vehicle and the connecting mode of orbital assembly, in which all modules are orbited fully loaded with propellant. The effect of a significant increase in nuclear engine specific impulse is discussed.
Harris, Ronald J.↗