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Simulation of the effects of the orbital debris environment on spacecraftA remedy for the lack of a technique for testing the effects of orbital debris impacts has been sought along two paths at Boeing and elsewhere, firstly through the development of new launcher techniques capable of impact velocities between 8 and 16 km/s and secondly through the development of similitude techniques for modeling 8 to 16 km/s impacts using the present capabilities of projectile launchers. These two approaches are briefly discussed.
Document ID
19890003236
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bjorkman, Michael D. (Boeing Aerospace Co. Seattle, WA, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1988
Publication Information
Publication: NASA, Goddard Space Flight Center, 15th Space Simulation Conference: Support the Highway to Space Through Testing
Subject Category
Spacecraft Design, Testing And Performance
Accession Number
89N12607
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19890003211Collected WorksFifteenth Space Simulation Conference: Support the Highway to Space Through Testing
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