ALBERT

All Library Books, journals and Electronic Records Telegrafenberg

X
feed icon rss

Your email was sent successfully. Check your inbox.

An error occurred while sending the email. Please try again.

Proceed reservation?

Export
Filter
  • Spacecraft Design, Testing and Performance  (3)
  • 2010-2014  (2)
  • 2005-2009  (1)
Collection
Keywords
Years
Year
  • 1
    facet.materialart.
    Unknown
    Multi-shock Shield Performance at 16.5 MJ for Catalogued Debris (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-19
    Description: While orbital debris of ten centimeters or more are tracked and catalogued, the difficulty of finding and accurately accounting for forces acting on the objects near the ten centimeter threshold results in both uncertainty of their presence and location. These challenges result in difficult decisions for operators balancing potential costly operational approaches with system loss risk. In this paper, numerical simulations and an experiment using the multishock shield system is described for a cylindrical projectile composed of Nylon, aluminum and void that is approximately 8 cm in diameter and 10 cm in length weighing 670 g impacting the multishock shield normal to the surface with approximately 16.5 MJ of kinetic energy. The multishock shield system has been optimized to facilitate the fragmentation, spread and deceleration of the projectile remnants using hydrodynamic simulations of the impact event. The characteristics and function of each of the layers of the multishock system will be discussed along with considerations for deployment and improvement.
    Keywords: Spacecraft Design, Testing and Performance
    Type: JSC-CN-30655 , International Astronautical Congress 2014; Sep 29, 2014 - Oct 03, 2014; Toronto, Ontario, Canada; Canada
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 2
    facet.materialart.
    Unknown
    Orion Spacecraft MMOD Protection Design and Assessment (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: 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.
    Keywords: Spacecraft Design, Testing and Performance
    Type: JSC-CN-23587 , American Physical Society Shock Physics Conference; Jun 29, 2011; Chicago, IL; United States
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 3
    facet.materialart.
    Unknown
    Ballistic Performance of Porous-Ceramic, Thermal-Protection-Systems (2009)
    In:  Other Sources
    Details
    Publication Date: 2019-07-19
    Description: Porous-ceramic, thermal protection systems are used heavily in current reentry vehicles like the Space Shuttle and are currently being proposed for the next generation of manned spacecraft, Orion. These materials insulate the structural components of a spacecraft against the intense thermal environments of atmospheric reentry. Furthermore, these materials are also highly exposed to space environmental hazards like meteoroid and orbital debris impacts. This paper discusses recent impact testing up to 9 km/s, and the findings of the influence of material equation-of-state on the simulation of the impact event to characterize the ballistic performance of these materials. These results will be compared with heritage models1 for these materials developed from testing at lower velocities. Assessments of predicted spacecraft risk based upon these tests and simulations will also be discussed.
    Keywords: Spacecraft Design, Testing and Performance
    Type: JSC-CN-18501 , Hypervelocity Impact Symposium 2010; Apr 11, 2010; Freiburg; Germany
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
Close ⊗
This website uses cookies and the analysis tool Matomo. More information can be found here...