Flexible Ablative Thermal Protection Sizing on Infl atable Aerodynamic Decelerator for Human Mars Entry Descent and Landing

Within its Entry, Descent and Landing Systems Analysis (EDL-SA) Project, NASA has been evaluating the technology investments required to enable human and large payload missions to Mars. In FY09 study was focused on Exploration-class cargo or crewed missions requiring 10 to 50 metric tons of landed payload. One of the deceleration concepts to achieve this goal employed a large Hypersonic Infla table Aerodynamic Decelerator (HIAD). The HIAD would execute both aerocapture and atmospheric entry maneuvers at Mars and would therefore require a Thermal Protection System (TPS) capable of enduring dual heat pulse environments at high heat flux. This would most likely require an ablative TPS. At the time of the study, no flexible materials existe d that met the estimated HIAD requirements. Based on current research, estimate d flexible ablator material properties were created and used for a TPS sizing analysis of a dual heat pulse HIAD. These properties were used to perform HIAD TPS sizing analysis and additional trade studies. These studies demonstrate that the development of flexible ablato rs will lead to reasonable TPS masses for Hypersonic Inflatable Aerodynamic Decelerators.