Apollo scientific data system /T4/S17/ Qualification test report
Apollo scientific data system /T4-S17/ environmental qualification tests
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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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Apollo X-ray astronomy experiment /S-17/ Qualification test report
Apollo X ray astronomy experiment qualification test program with test data
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A solar simulator used for pre-flight thermal qualification of the RAE-A spacecraft
Solar simulator for preflight thermal qualification of RAE-A spacecraft
Lester, D. L.↗
The study of infrared evaluation in qualification and failure analysis of semiconductor devices Interim progress report, 28 Apr. - 28 Jul. 1968
Infrared display techniques and acceptance criteria for microcircuit qualification and semiconductor device failure analysis
Berger, W. M.↗
Engineering and operational experiences related to lunar-surface thermal-vacuum qualification of the Apollo extravehicular mobility unit.
Manned testing of EVA equipment in thermal-vacuum environment for qualification of Apollo extravehicular mobility unit, using lunar surface thermal simulator
Maples, H. E.↗
Development of qualification test program for microelectronic devices Final report, 1 Nov. 1968 - 3 Jul. 1969
Qualification test program for digital monolithic integrated circuit devices
Binelli, W. D.↗
The Professional and Technical Qualifications of Apollo Project Managers
Qualifications of Apollo project manager personnel
Cicero, J. P.↗
Development of Biosatellite Primate Mission component qualification levels
Biosatellite Primate Mission component qualifications
Abrams, E. M.↗
Development of Biosatellite Primate Mission component qualification levels
Biosatellite Primate Mission Program for component qualification levels validated by flight tests data, performing vibration tests on prime structure spacecraft
Abrams, E. M.↗
Qualification and testing of an electrically propelled spacecraft - SERT 2
Qualification and testing of electric propulsion system for SERT 2 spacecraft
De Pauw, J. F.↗
IMP-1-D-4.5.5 - Description and summary of qualification testing of the IMP-1 attitude control system and Yo-Yo despin system
Results and description of qualification tests of attitude control system and yo-yo despin system in flight configuration as installed on IMP-1 spacecraft
Metzger, J. R.↗
Qualification evaluation of the tower jettison motor for the Apollo spacecraft program launch escape system
Qualification tests of tower jettison motors for Apollo spacecraft program launch escape systems
Lee, B. J.↗
Qualification testing - Space vehicle design criteria
Qualification tests conducted on flight quality components, subsystems, and systems to prove that structural design requirements have been achieved
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Low-frequency vibration qualification testing for Mariner Mars 1971 propellant tanks
LF vibration qualification tests for Mariner Mars 1971 propellant tanks
Epstein, S. J.↗
Qualification test unit slide stainer (Beckman P/N 673753)
Specifications for a slide stainer unit for the Skylab program are presented. The qualification test slide stainer was designed to be a self-contained system capable of performing an eight-step Gram stain of microorganisms and a Wright's stain of blood smears.
Bernier, P. S.↗
Postflight simulation of parachute deployment dynamics of Viking qualification flight tests
Simulation calculations of the Viking qualification flight tests are conducted by use of analytical models of the parachute deployment dynamics process. Results from the study indicate that good simulations of event times and trajectory are obtained. If the full-scale parachute drag coefficient is used, a good simulation of first opening load is obtained and the overall nature of the load history is calculated. For longitudinal motions, the two-degree-of-freedom models give good agreement with a six-degree-of-freedom model. It is believed that the analytical models used are tools which will aid in the analysis of future flight systems.
Whitlock, C. H.↗
Qualification flight tests of the Viking decelerator system.
The Balloon Launched Decelerator Test (BLDT) series conducted at White Sands Missile Range (WSMR) during July and August of 1972 flight qualified the NASA Viking '75 decelerator system at conditions bracketing those expected for Mars. This paper discusses the decelerator system design requiremnts, compares the test results with prior work, and discusses significant considerations leading to successful qualification in earth's atmosphere. The Viking decelerator system consists of a single-stage mortar-deployed 53-foot nominal diameter disk-gap-band parachute. Full-scale parachutes were deployed behind a full-scale simulated Viking vehicle at Mach numbers from 0.47 to 2.18 and dynamic pressures from 6.9 to 14.6 psf. Analyses show that the system is qualified with sufficient margin to perform successfully for the Viking mission.
Moog, R. D.↗
The Viking mortar - Design, development, and flight qualification.
Approximately 25,400 ft above the local surface of Mars, a radar height sensor fires the Viking mortar, which ejects a 53-ft D sub o disk-gap-band (DGB) parachute. The parachute decelerates and stabilizes the Viking lander sufficiently for the terminal engine system to take over and effect a soft landing. The general design and environmental requirements for the mortar system are presented; various illustrations of the mortar components and how the mortar system functions also are presented. Primary emphasis is placed on manufacturing, developing, and qualification testing of the mortar system.
Brecht, J. P.↗