Carbon-phenolic ablative materials for re-entry space vehicles: plasma wind tunnel test and finite element modeling

Author:

Paglia L.ORCID,Tirillò J.,Marra F.,Bartuli C.,Simone A.,Valente T.,Pulci G.

Publisher

Elsevier BV

Subject

Mechanical Engineering,Mechanics of Materials,General Materials Science

Reference30 articles.

1. Navier–stokes simulations of hypersonic flows with coupled graphite ablation;Bianchi;J. Spacecr. Rocket.,2010

2. Thermal Protection System Technology and Facility Needs for Demanding Future Planetary Missions;Laub,2003

3. Numerical simulation of oxy-acetylene testing procedure of ablative materials for re-entry space vehicles;Marra;Proc. MechE,2010

4. Updated ablation and thermal response program for spacecraft heatshield analysis;Milos;J. Spacecr. Rocket.,1999

5. Ablative properties of carbon black and MWNT/phenolic composites: a comparative study;Natali;Composites Part A,2012

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