HVI Ballistic Limit Characterization of Fused Silica Thermal PanesFused silica window systems are used heavily on crewed reentry vehicles, and they are currently being used on the next generation of US crewed spacecraft, Orion. These systems improve crew situational awareness and comfort, as well as, insulating the reentry critical components of a spacecraft against the intense thermal environments of atmospheric reentry. Additionally, these materials are highly exposed to space environment hazards like solid particle impacts. This paper discusses impact studies up to 10 km/s on a fused silica window system proposed for the Orion spacecraft. A ballistic limit equation that describes the threshold of perforation of a fuse silica pane over a broad range of impact velocities, obliquities and projectile materials is discussed here.
Document ID
20150001651
Acquisition Source
Johnson Space Center
Document Type
Conference Paper
Authors
Miller, J. E. (Texas Univ. El Paso, TX, United States)
Bohl, W. D. (Lockheed Martin Corp. Houston, TX, United States)
Christiansen, E. L. (NASA Johnson Space Center Houston, TX, United States)
Davis, B. A. (Jacobs Technology, Inc. Houston, TX, United States)
Deighton, K. D. (Lockheed Martin Corp. Houston, TX, United States)