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Penetration experiments in aluminum 1100 targets using soda-lime glass projectilesThe cratering and penetration behavior of annealed aluminum 1100 targets, with thickness varied from several centimeters to ultra-thin foils less than 1 micrometer thick, were experimentally investigated using 3.2 mm diameter spherical soda-lime glass projectiles at velocities from 1 to 7 km/s. The objective was to establish quantitative, dimensional relationships between initial impact conditions (impact velocity, projectile diameter, and target thickness) and the diameter of the resulting crater or penetration hole. Such dimensional relationships and calibration experiments are needed to extract the diameters and fluxes of hypervelocity particles from space-exposed surfaces and to predict the performance of certain collisional shields. The cratering behavior of aluminum 1100 is fairly well predicted. However, crater depth is modestly deeper for our silicate impactors than the canonical value based on aluminum projectiles and aluminum 6061-T6 targets. The ballistic-limit thickness was also different. These differences attest to the great sensitivity of detailed crater geometry and penetration behavior on the physical properties of both the target and impactor. Each penetration experiment was equipped with a witness plate to monitor the nature of the debris plume emanating from the rear of the target. This plume consists of both projectile fragments and target debris. Both penetration hole and witness-plate spray patterns systematically evolve in response to projectile diameter/target thickness. The relative dimensions of the projectile and target totally dominate the experimental products documented in this report; impact velocity is an important contributor as well to the evolution of penetration holes, but is of subordinate significance for the witness-plate spray patterns.
Document ID
19960008824
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Horz, Friedrich (NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Cintala, Mark J. (NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Bernhard, Ronald P. (Lockheed Engineering and Sciences Co. Houston, TX., United States)
Cardenas, Frank (Lockheed Engineering and Sciences Co. Houston, TX., United States)
Davidson, William E. (Lockheed Engineering and Sciences Co. Houston, TX., United States)
Haynes, Gerald (Lockheed Engineering and Sciences Co. Houston, TX., United States)
See, Thomas H. (Lockheed Engineering and Sciences Co. Houston, TX., United States)
Winkler, Jerry L. (Lockheed Engineering and Sciences Co. Houston, TX., United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1995
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NAS 1.15:104813
S-801
NASA-TM-104813
Accession Number
96N15990
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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