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.