Temperature effects on bumper hole diameter for impact velocities from 2 to 7 km/s

International Journal of Impact Engineering

Volumn 29, Issue 1-10, 2003, Pages 487-495

  Myers, Brooke A ^a   Schonberg, William P ^b   Williamsen, Joel E ^c  

^a University of Denver   (United States)

^b Architectural and Environmental Engineering   (United States)

^c INSTITUTE FOR DEFENSE ANALYSES   (United States)

Author keywords

Hole diameter; Hypervelocity impact; Orbital debris; Spacecraft shielding; Temperature effects

Indexed keywords

HOLE DIAMETER; HYPERVELOCITY IMPACT; ORBITAL DEBRIS; SPACECRAFT SHIELDING;

CORRELATION METHODS; HEATING; REGRESSION ANALYSIS; SHIELDING; SPACE DEBRIS; SPACE STATIONS; SPACECRAFT; THERMAL EFFECTS;

IMPACT TESTING;

EID: 2342507764     PISSN: 0734743X     EISSN: None     Source Type: Journal    
DOI: 10.1016/j.ijimpeng.2003.09.044     Document Type: Conference Paper

References (4)

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2. Housen KR, Schmidt RM. Hole Size From Impacts at Simulated Velocities to 23 km/s. Int. J. Impact Engng., 1997;20:399-410.
3. Nysmith CR. Penetration Resistance of Double Sheet Structures at Velocities to 8.8 km/sec. NASA TN-D-4568, 1968.
4. Maiden CJ, McMillan AR, Sennett RE. Investigation of Fundamental Mechanism of Damage to Thin Targets by Hypervelocity Projectiles. General Motors Corporation Final Report No. TR63-225, GM Defense Research Laboratories, Santa Barbara, CA, 1963.