HVI Ballistic Limit Charaterization of Fused Silica Thermal PaneThe Orion spacecraft's windows are exposed to the micrometeroid and orbital debris (MMOD) space environments while in space as well as the Earth entry environment at the mission's conclusion. The need for a low-mass spacecraft window design drives the need to reduce conservatism when assessing the design for loss of crew due to MMOD impact and subsequent Earth entry. Therefore, work is underway at NASA and Lockheed Martin to improve characterization of the complete penetration ballistic limit of an outer fused silica thermal pane. Hypervelocity impact tests of the window configuration at up to 10 km/s and hydrocode modeling have been performed with a variety of projectile materials to enable refinement of the fused silica ballistic limit equation.
Document ID
20140006471
Acquisition Source
Johnson Space Center
Document Type
Abstract
Authors
Bohl, William E. (Lockheed Martin Space Systems Co. Denver, CO, United States)
Miller, Joshua E. (Jacobs Technology, Inc. Houston, TX, United States)
Christiansen, Eric L. (NASA Johnson Space Center Houston, TX, United States)
Deighton, Kevin. (Lockheed Martin Space Systems Co. Denver, CO, United States)
Davis, Bruce (Jacobs Technology, Inc. Houston, TX, United States)