Statistics – Applications
Scientific paper
Jan 2002
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002aipc..608..337l&link_type=abstract
SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM- STAIF 2002. Conference on Thermophyiscs in Microgravity; Conference on In
Statistics
Applications
Ceramics And Refractories, Spaceborne And Space Research Instruments, Apparatus, And Components, New Materials: Theory, Design, And Fabrication
Scientific paper
Many planetary probes, landers and aerocapture concepts are conceived for entry trajectories where peak convective heat flux is in the range 150-400 W/cm2. This may be too severe an environment for either reusable or low-density ablative materials. The high-density ablatives will work in such environments but the associated TPS weight requirements can be prohibitive. Unfortunately, there are few, if any, well-understood materials that provide reliable, predictable ablative performance for the 150-400 W/cm2 regime while still providing weight efficient TPS solutions. JPL has recently been evaluating an Earth aerocapture demonstration at an entry velocity of ~10 km/s. TPS thickness and areal weight requirements were determined for current ablative TPS candidates (e.g., SLA-561V, PICA) where, for the large integrated heat loads associated with aerocapture, it is shown that some of these materials may not provide efficient thermal protection. A new concept, employing a low catalycity, high emissivity coating on a low-density ceramic tile is evaluated and shown to provide significant benefits for such missions. .
No associations
LandOfFree
New TPS materials for aerocapture does not yet have a rating. At this time, there are no reviews or comments for this scientific paper.
If you have personal experience with New TPS materials for aerocapture, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and New TPS materials for aerocapture will most certainly appreciate the feedback.
Profile ID: LFWR-SCP-O-1086289