A New Method for Estimating the Mass Recession Rate for Ablator Systems

Authors: Bianca A. Szasz, Keiichi Okuyama

Abstract:

As the human race will continue to explore the space by creating new space transportation means and sending them to other planets, the enhance of atmospheric reentry study is crucial. In this context, an analysis of mass recession rate of ablative materials for thermal shields of reentry spacecrafts is important to be carried out. The paper describes a new estimation method for calculating the mass recession of an ablator system made of carbon fiber reinforced plastic materials. This method is based on Arrhenius equation for low temperatures and, for high temperatures, on a theory applied for the recession phenomenon of carbon fiber reinforced plastic materials, theory which takes into account the presence of the resin inside the materials. The space mission of USERS spacecraft is considered as a case study.

Keywords: Ablator system, mass recession, spacecraft, atmospheric reentry.

Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1096809

References:

[1] Alexandre Martin, Iain D. Boyd, Ioana Cozmuta and Michael J. Wright, “Chemistry model for ablating carbon-phenolic material during atmospheric re-entry”, 48th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, AIAA 2010-1175, Orlando, Florida.
[2] Keiichi Okuyama, Sumio Kato and Hiroaki Ohya, “Thermochemical Performance of a Lightweight Charring Carbon Fiber Reinforced Plastic”, Trans. Japan Soc. Aero. Space Sci., Vol.56, No.3, pp. 159-169, 2013.
[3] Robert L. Potts, “Analysis of an Integral Method for Computing Reentry Vehicle Heat Conduction in Systems Level Computer Codes”, Science Applications, Inc., El Segundo, California.
[4] Keiichi Okuyama, Sumio Kato and Tetsuya Yamada, “Thermo-chemical recession characteristics of CFRP in an earth atmospheric reentry environment”, TANSO, 219 (2005), pp. 232-237 (in Japanese).
[5] J.W. Metzger, M.J. Enge and N.S. Diaconis, “Oxidation and Sublimation of Graphite”, AIAA J., 5, 3 (1967), pp.451-460.
[6] Robert L. Potts, “Application of Integral Methods to Ablation Charring Erosion”, A Review, Journal of Spacecraft and Rockets, Vol.32, No.2, March-April 1995.