Orion Spacecraft MMOD Protection Design and Assessment
- Author
- Davis, B. Alan
- Published
- [2011].
- Physical Description
- 1 electronic document
- Additional Creators
- Bohl, William E., Miller, Joshua E., Christiansen, Eric, and Foreman, Cory D.
Online Version
- hdl.handle.net , Connect to this object online.
- Restrictions on Access
- Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access - Summary
- A first-principals, semi-empirical ballistic performance model has been developed for porous ceramics. Lightweight thermal protection systems protect the crew and vehicle of orbital and exo-orbital missions from the intense heat of atmospheric reentry. To maintain low launch weights these materials are their own protection from space hazards like orbital debris and meteoroids. A ballistic performance model is described here that models the performance under a variety of impact conditions. Using the model described here relative to an energy scaled model results in a significantly reduced prediction of full penetration of this material at ISS orbital parameters.
- Other Subject(s)
- Collection
- NASA Technical Reports Server (NTRS) Collection.
- Note
- Document ID: 20110011340.
JSC-CN-23587.
American Physical Society Shock Physics Conference; 29 Jun. 2011; Chicago, IL; United States. - Terms of Use and Reproduction
- Copyright, Distribution as joint owner in the copyright.
View MARC record | catkey: 15991070