Implications of shock effects in iron meteorites.
Shock loading history effect on solid state response of iron meteorites to annealing at moderate temperatures permits deductions about thermal history
Jain, A. V.↗
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Shock-induced preferred disorder in solids.
X ray detectable preferred disorder in solids by shock loading studied in Ainsworth meteorite and in hexagonal alpha silicon dioxide
Jaeger, R. R.↗
Preparation of simulated lunar samples Final report
Techniques for shock loading and recovering mineral samples in simulated lunar conditions
De Carli, P. S.↗
A small ballistic range for impact metamorphism studies
Experimental ballistic range for shock loading of rock materials
Hoerz, F.↗
Shock deformation of Inconel 600 alloy - Effect of fine coherent precipitates on explosive-shock hardening
Coherent precipitates effect on explosive shock hardening of pure nickel and Inconel alloy sandwich assemblies determined from simultaneous shock loading at specific pressures
Foltz, J. V.↗
Erasure fission tracks in glasses and silicates by shock waves
Erasure fission tracks in soda-lime glass, tektite, biotite and apatite by shock loading, determining dynamic pressure and associated temperature effects
Ahrens, T. J.↗
On preferred disorder and the shock history of chemical group IVA meteorites
Preferred disorder and shock histories of chemical group 4A meteorites from metallographic and X ray diffraction, discussing preterrestrial shock loading
Jain, A. V.↗
Aerospace systems pyrotechnic shock data - Ground test and flight. Volume 1 - Summary and analysis Final report, Jun. 1968 - Mar. 1970
Characteristics of shock loads on spacecraft structures produced by pyrotechnics and explosive devices - Vol. 1
Kacena, W. J., III↗
Aerospace systems pyrotechnic shock data /ground test and flight/. Volume 3 - Data Final report, Jun. 1968 - Mar. 1970
Determination of shock loads on spacecraft structures created by explosive separation of components - Vol. 3
Kacena, W. J., III↗
Aerospace systems pyrotechnic shock data /ground test and flight/. Volume 4 - Lockheed data and analyses Final report, Jun. 1968 - Mar. 1970
Compilation of shock loads on spacecraft structures produced by actuation of pyrotechnics and explosive devices - Vol. 4
Kacena, W. J., III↗
Aerospace systems pyrotechnic shock data /ground test and flight/. Volume 5 - Lockheed data and analyses Final report, Jun. 1968 - Mar. 1970
Characteristics of shock loads induced on spacecraft structures by initiation of explosive pin pullers - Vol. 5
Kacena, W. J., III↗
Aerospace systems pyrotechnic shock data /ground test and flight/. Volume 6 - Pyrotechnic shock design guidelines manual, revision A Final report, Jun. 1968 - Mar. 1970
Design of structures and equipment to reduce shock loads induced by pyrotechnics and explosive devices - Vol. 6
Kacena, W. J., III↗
Shock and vibration tests of a SNAP 8 turboalternator
Turboalternator for SNAP 8 power system subjected to expected vehicle launch vibration and shock loading
Foley, R. S.↗
Wind tunnel model damper
Damper system for alleviating air flow shock loads on wind tunnel models.
Bryan, M. B.↗
Comparison of the substructures and properties of nickel, TD-Ni, Chromel-A, Inconel 600, and TD-NiCr following explosive-shock deformation
Substructures and properties of Ni, Chromel A, Inconel 600 and TD-NiCr following explosive shock load deformation, using electron microscope
Foltz, J. V.↗
An inventory of aeronautical ground research facilities. Volume 3: Structural
An inventory of test facilities for conducting acceleration, environmental, impact, structural shock, load, heat, vibration, and noise tests is presented. The facility is identified with a description of the equipment, the testing capabilities, and cost of operation. Performance data for the facility are presented in charts and tables.
Pirrello, C. J.↗
Shock and vibration tests of a SNAP-8 NaK pump
The pump used for reactor cooling in the SNAP 8 space power system was subjected to the expected vehicle launch vibration, and shock loading in accordance with the SNAP 8 environmental specification. Subsequent disassembly revealed damage to the thrust bearing pins, which should be redesigned and strengthened. The unit was operational, however, when run in a test loop after reassembly.
Stromquist, A. J.↗
Performance of the CSM RCS during the AS 506/CSM 107/LM 5 mission (Apollo 11)
The Apollo 11 service module and the command module (CM) reaction control system performed satisfactorily throughout the mission. Two anomalies which occurred were an inadvertent isolation valve closure during command and service module/Saturn S4B/lunar module separation and a failure of a CM thruster to respond to automatic commands. The isolation valves were later opened by the crew and remained open during the remainder of the mission. The cause of the closure was determined to be the shock loads generated during separation. The CM engine malfunction was caused by a faulty terminal board connector. All system parameters were normal during the mission, and all mission requirements were satisfied.
Lingle, W. N.↗