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HVI Ballistic Performance Characterization of Non-Parallel WallsThe Double-Wall, "Whipple" Shield [1] has been the subject of many hypervelocity impact studies and has proven to be an effective shield system for Micro-Meteoroid and Orbital Debris (MMOD) impacts for spacecraft. The US modules of the International Space Station (ISS), with their "bumper shields" offset from their pressure holding rear walls provide good examples of effective on-orbit use of the double wall shield. The concentric cylinder shield configuration with its large radius of curvature relative to separation distance is easily and effectively represented for testing and analysis as a system of two parallel plates. The parallel plate double wall configuration has been heavily tested and characterized for shield performance for normal and oblique impacts for the ISS and other programs. The double wall shield and principally similar Stuffed Whipple Shield are very common shield types for MMOD protection. However, in some locations with many spacecraft designs, the rear wall cannot be modeled as being parallel or concentric with the outer bumper wall. As represented in Figure 1, there is an included angle between the two walls. And, with a cylindrical outer wall, the effective included angle constantly changes. This complicates assessment of critical spacecraft components located within outer spacecraft walls when using software tools such as NASA's BumperII. In addition, the validity of the risk assessment comes into question when using the standard double wall shield equations, especially since verification testing of every set of double wall included angles is impossible.
Document ID
20120000710
Acquisition Source
Johnson Space Center
Document Type
Conference Paper
Authors
Bohl, William
(Lockheed Martin Space Systems Co. Denver, CO, United States)
Miller, Joshua
(Lockheed Martin Space Systems Co. Denver, CO, United States)
Christiansen, Eric
(NASA Johnson Space Center Houston, TX, United States)
Date Acquired
August 25, 2013
Publication Date
January 1, 2012
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
JSC-CN-25496
Meeting Information
Meeting: 2012 Hypervelocity Impact Symposium (HVIS 2012)
Location: Baltimore, MD
Country: United States
Start Date: September 16, 2012
End Date: September 20, 2012
Sponsors: Hypervelocity Impact Society
Distribution Limits
Public
Copyright
Public Use Permitted.
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