Saturn S-IB stage Final static test report, stage S-IB-4
Acceptance static test firing data for Saturn flight stage S-IB-4
ROCKET FIRING↗
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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.
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Analysis of empirical sound fields
Statistical analysis of empirical sound fields propagated from static test firing of large space booster power plants
NOISE ATTENUATION↗
Experimental evaluation of six ablative-material thrust chambers as components of storable-propellant rocket engines
Test firing evaluation of six ablative-material thrust chambers as components of storable propellant rocket engines
COMBUSTION CHAMBER↗
Infrared spectroradiometer for rocket exhaust analysis
Infrared spectroradiometer measures high-resolution spectral absorption, emission, temperature, and concentration of chemical species in radically symmetric zones of the exhaust plumes of large rocket engines undergoing static firing tests. Measurements are made along predetermined lines of sight through the plume.
Herget, W. F.↗
Two hundred sixty SL-3 motor program Final report
Design, fabrication, and test firing of 260 inch diameter solid rocket engine
Source record↗
Radio astronomy Explorer apogee kick motor Final report, 5 May 1966 - 31 Mar. 1967
Design, development, and static firing tests of apogee kick motor for Radio Astronomy Explorer Satellite
Jones, H. G.↗
Recent Measurements at JPL of Particle Size of Aluminum Oxide from Small Rocket Motors
Small rocket engine test firings conducted to measure particle size distribution of aluminum oxide exhausts
Dobbins, R. A.↗
The operational method used to determine far- field sound propagation from the atmospheric data at the NASA Mississippi Test Facility.
Far field sound propagation during Apollo Saturn space vehicle stage static test firing, defining sound intensity for given set of atmospheric parameters
Nybo, L. W.↗
Test of improved ignitor for first stage separation rockets for the Atlas-Centaur launch vehicle
Development and test firing of improved igniter for first stage retrorockets of Atlas Centaur launch vehicle
Heath, R. W.↗
The post-test analysis of ablative materials Final report, 11 Jul. 1967 - 15 May 1968
Ablative materials examination before and after test firing
Burrell, B. W.↗
Development of cost-optimized insulation system for use in large solid rocket motors. Volume 3, task 3 - Material performance determination Final report
Test firing evaluation of materials to develop cost optimized insulation system for large solid rocket motors
Nachbar, D. L.↗
NASA rocket motor defects investigation. Volume 1 - Technical investigation Comprehensive report, Aug. 1966 - Jun. 1968
Static firing tests to reduce glass fiber defects and to improve field repair work on X-248 rocket motor cases
Enie, R. B.↗
NASA rocket motor defects investigation. Volume 2 - Tables and figures Comprehensive report, Aug. 1966 - Jun. 1968
Static firing tests to reduce glass fiber defects and to improve field repair work on X-248 rocket motor case - Supporting tables and figures
Enie, R. B.↗
An empirically derived erosion law and its application to Lunar Module landing.
Module landing effects on lunar surface, deriving erosion law from Surveyor 5 engine firing test and vacuum test data
Mason, C. C.↗
Volumetric calibration of a propellant utilization system
Method of calibrating capacitance-type propellant mass sensors provides meaningful mass units accurate to within one percent of the total load. Neither special propellant loading nor test firing is required. Recalibration of the system is possible without special propellant loading. This method provides increased flexibility for vehicle operation.
Lenning, J. J.↗
Refractory composite materials for spacecraft thrust chambers Final report, 23 Jul. 1968 - 22 Feb. 1970
Hot firing tests with FLOX/methane propellants for evaluating pyrolytic refractory composite materials for thrust chambers
Campbell, J. G.↗
Space storable thruster investigation
Design, characteristics, and test firing of radiation and film cooled 25 pound thrust graphitic thrust chamber with liquid cryogenic propellants
Campbell, J. G.↗
High-pressure gaseous hydrogen/gaseous oxygen thruster
High pressure gaseous hydrogen oxygen auxiliary propulsion systems /APS/ thrustor design and cold flow and hot fire testing for space shuttle requirements
Domokos, S. J.↗