NASA has successfully developed a new and innovative Heatshield for Extreme Entry Environments Technology, or HEEET, which, at a Technology Readiness Level (TRL) of 6, is ready for use in Ice Giant missions. HEEET is not just a replacement for the legacy full-density carbon-phenolic (FDCP) material, which was used in NASA's Pioneer-Venus and Galileo missions; it is also a more mass efficient and robust alternative, and a technology that has a sustainable manufacturing base. HEEET is a dual-layer, 3-dimensionally woven material. It has a dense outer layer, made of pure carbon fibers, that comes into contact with and protects against extreme entry environments. Below this layer is an integrally woven, lower density insulating layer, made of a blend of carbon and phenolic yarn, that reduces heat-conduction to the carrier structure. The present paper describes development of this material, its thermal, structural, and aerothermal testing, production of an engineering test unit at flight scale, and maturation for infusion into missions to various planetary destinations, with a focus on Ice Giant in situ missions. Finally, for representative entry velocities at Uranus and Neptune, and a range of entry masses and flight path angles, margined thicknesses of HEEET are computed. When the limits of heat fluxes and pressures that can be achieved in ground-test facilities, and loom limits, are imposed on these thickness estimates, it is shown that several atmospheric entry missions are possible at the two destinations.

This poster provides an overview of the requirements, design, development and testing of the 3D Woven TPS being developed under NASAs Heatshield for Extreme Entry Environment Technology (HEEET) project. Under this current program, NASA is working to develop a Thermal Protection System (TPS) capable of surviving entry into Saturn. A primary goal of the project is to build and test an Engineering Test Unit (ETU) to establish a Technical Readiness Level (TRL) of 6 for this technology by 2018. Poster also discusses use of HEEET TPS for probe missions to the Ice Giants, Uranus and Neptune.

A finite volume, fully implicit ablation and thermal response code that simulates the pyrolysis gas flow, thermochemical ablation, and shape change of thermal protection materials and systems in multiple dimensions is developed. Both structured and unstructured grid approaches are implemented. The governing equations (which include energy conservation, pyrolysis gas mass conservation with Darcy's law, a multicomponent decomposition model, and a surface energy balance) are solved with a moving grid system to simulate the response of charring ablators in aerothermal heating environments. This work demonstrates and validates new capabilities that are added to the code. These expanded capabilities include fully implicit time integration, pyrolysis gas flow due to Darcy's law, an unstructured grid option, and parallel computing. Three groups of test cases that consider three different charring ablators are presented. In the first group, three-dimensional iso-q-shaped phenolic-impregnated carbon ablator test models with various throughthickness conductivity directions are studied. In the second group, axisymmetric flat-faced dual-layer woven carbon phenolic models are examined. Finally, in the third group, axisymmetric iso-q-shaped three-dimensional multifunctional ablative thermal protection system models are analyzed. For all cases, predictions are compared with available temperature data.

A new dual-layer carbon phenolic manufactured from a three-dimensional woven substrate was tested in three arcjet facilities over a range of environments up to heat flux of approximately 6 k W/cm(2) at pressure of 5 bar. Sample geometries included both stagnation and wedge models. Based on property measurements and the observed material response, a midfidelity thermal response and ablation model was developed. The material and tests are described, and predictions of recession and temperature are compared with the arcjet test data.

This presentation introduces a new sizing and margin methodology for dual-layer Thermal Protection Systems (TPS). The methodology has been tailored for application to a dual-layer 3D-woven TPS called Heat-shield for Extreme Entry Environments Technology (HEEET). Sizing is performed for a reference Saturn probe mission to show how uncertainties in trajectory, aerothermal modelling and TPS response impact the sizing of each layer.

The present work provides the results of a short exploratory study on the performance of Phenolic Impregnated Carbon Ablator, or PICA, at high heat flux and pressure in an arcjet facility at NASA Ames Research Center. The primary objective of the study was to explore the thermal response of PICA at cold-wall heat fluxes well in excess of 1500 W/cm (exp 2). Based on the results of a series of flow simulations, multiple PICA samples were tested at an estimated cold wall heat flux and stagnation pressure of 1800 W/cm (exp 2) and 130 kPa, respectively. All samples survived the test, and no failure was observed either during or after the exposure. The results indicate that PICA has a potential to perform well at environments with significantly higher heat flux and pressure than it has currently been flown.

This poster provides an overview of the requirements, design, development and testing of the 3D Woven TPS being developed under NASAs Heatshield for Extreme Entry Environment Technology (HEEET) project. Under this current program, NASA is working to develop a Thermal Protection System (TPS) capable of surviving entry into Saturn. A primary goal of the project is to build and test an Engineering Test Unit (ETU) to establish a Technical Readiness Level (TRL) of 6 for this technology by 2017.

A new conformal type of phenolic impregnated carbon ablator was manufactured by resin impregnation of carbon felt. Based on property measurements of the conformal material and the existing model for a standard, rigid phenolic impregnated carbon ablator, a midfidelity material response model for the conformal material was developed. The rigid and conformal materials were arcjet tested simultaneously on a sphere-cone geometry in several environments with frustum heat flux up to 380W/cm2. Good agreement between the predictions and data was obtained for recession, surface temperature, and in-depth temperatures. The conformal material has a slightly greater ablation rate but significantly lower thermal diffusivity than the rigid material.

This poster provides an overview of the requirements, design, development and testing of the 3D Woven TPS being developed under NASA's Heatshield for Extreme Entry Environment Technology (HEEET) project. Under this current program, NASA is working to develop a Thermal Protection System (TPS) capable of surviving entry into Venus or Saturn. A primary goal of the project is to build and test an Engineering Test Unit (ETU) to establish a Technical Readiness Level (TRL) of 6 for this technology by 2017.

ADEPT is an atmospheric entry architecture for missions to most planetary bodies with atmospheres: Current Technology development project funded under STMD Game Changing Development Program (FY12 start); stowed inside the launch vehicle shroud and deployed in space prior to entry; low ballistic coefficient (less than 50 kilograms per square meter) provides a benign deceleration and thermal environment to the payload; High-temperature ribs support three dimensional woven carbon fabric to generate drag and withstand high heating.

In 2011, NASAs Aeronautics Research Mission Directorate (ARMD) funded an effort to develop an ablative thermal protection system (TPS) material that would have improved properties when compared to Phenolic Impregnated Carbon Ablator (PICA) and AVCOAT. Their goal was a conformal material, processed with a flexible reinforcement that would result in similar or better thermal characteristics and higher strain-to-failure characteristics that would allow for easier integration on flight aeroshells than then-current rigid ablative TPS materials. In 2012, NASAs Space Technology Mission Directorate (STMD) began funding the maturation of the best formulation of the game changing conformal ablator, C-PICA. Progress has been reported at IPPW over the past three years, describing C-PICA with a density and recession rates similar to PICA, but with a higher strain-to-failure which allows for direct bonding and no gap fillers, and even more important, with thermal characteristics resulting in half the temperature rise of PICA. Overall, C-PICA should be able to replace PICA with a thinner, lighter weight, less complicated design. These characteristics should be particularly attractive for use as backshell TPS on high energy planetary entry vehicles. At the end of this year, the material should be ready for missions to consider including in their design, in fact, NASAs Science Mission Directorate (SMD) is considering incentivizing the use of C-PICA in the next Discovery Proposal call. This year both scale up of the material to large (1-m) sized pieces and the design and build of small probe heatshields for flight tests will be completed. NASA, with an industry partner, will build a 1-m long manufacturing demonstration unit (MDU) with a shape based on a mid LD lifting body. In addition, in an effort to fly as you test and test as you fly, NASA, with a second industry partner, will build a small probe to test in the Interactive Heating Facility (IHF) arc jet and, using nearly the same design, build the aeroshell and TPS, with instrumentation, for a small probe flight test article, due to fly in 2017. At the end of the year, the C-PICA will be at TRL 5+, and with the flight data in 2017, it will be at TRL 9 for missions needs with C-PICA at a small scale (12 diameter). The scale-up and small probe efforts will be de-scribed in this presentation.

Future NASA robotic missions utilizing an entry system into Venus and the outer planets, results in extremely high entry conditions that exceed the capabilities of state of the art low to mid density ablators such as PICA or AVCOAT. Previously, mission planners had to assume the use of fully dense carbon phenolic heatshields similar to what was flown on Pioneer Venus or Galileo. Carbon phenolic is a robust TPS material, however, its high density and relatively high thermal conductivity constrain mission planners to steep entries, with high heat fluxes and pressures and short entry durations. The high entry conditions pose challenges for certification in existing ground based test facilities and the longer-term sustainability of CP will continue to pose challenges. NASA has decided to invest in new technology development rather than invest in reviving carbon phenolic. The HEEET project, funded by STMD is maturing a game changing Woven Thermal Protection System technology. HEEET is a capability development project and is not tied to a single mission or destination, therefore, it is challenging to complete ground testing needed to demonstrate a capability that is much broader than any single mission or destination would require. This presentation will status HEEET progress. Near term infusion target for HEEET is the upcoming New Frontiers (NF-4) class of competitively selected Science Mission Directorate (SMD) missions for which it is incentivized.

Felt reusable surface insulation was used extensively on leeward external surfaces of the shuttle Orbiter, where the material is reusable for temperatures up to 670K. For application on leeward surfaces of the Orion multipurpose crew vehicle, where predicted temperatures reach 1620K, the material functions as a pyrolyzing conformable ablator. An arcjet test series was conducted to assess the performance of multilayer felt reusable surface insulation at high temperatures, and a thermal-response, pyrolysis, and ablation model was developed. Model predictions compare favorably with the arcjet test data.

During previous work at NASA Ames Research Center, most ablation predictions were obtained using a species thermodynamics database derived primarily from the JANAF thermochemical tables. However, the chemical equilibrium with applications thermodynamics database, also used by NASA, is considered more up to date. In this work, ablation analyses were performed for carbon and carbon phenolic materials using both sets of species thermodynamics. The ablation predictions are comparable at low and moderate heat fluxes, where the dominant mechanism is carbon oxidation. For high heat fluxes where sublimation is important, the predictions differ, with the chemical equilibrium with applications model predicting a lower ablation rate. The disagreement is greater for carbon phenolic than for carbon, and this difference is attributed to hydrocarbon species that may contribute to the ablation rate. Sample calculations for representative Orion and Stardust environments show significant differences only in the sublimation regime. For Stardust, if the calculations include a nominal environmental uncertainty for aeroheating, then the chemical equilibrium with applications model predicts a range of recession that is consistent with measurements for both heatshield cores.

In previous work, the authors documented the Multicomponent Ablation Thermochemistry (MAT) and the Fully Implicit Ablation and Thermal response (FIAT) programs. In this work, key features from MAT and FIAT were combined to create the new Fully Implicit Ablation, Thermal response, and Chemistry (FIATC) program. FIATC is fully compatible with FIAT (version 2.6) but has expanded capabilities to compute the multispecies surface chemistry and ablation rate as part of the surface energy balance. This new methodology eliminates B' tables, provides blown species as a function of time, and enables calculations that would otherwise be impractical (tables with 4 or more independent variables) or impossible (such as stacked pyrolyzing ablators). Equations and solution procedures are presented, then representative calculations of equilibrium and non-equilibrium ablation in flight and ground-test environments are discussed. Nomenclature

Covers advancements in spacecraft and tactical and strategic missile systems, including subsystem design and application, mission design and analysis, materials and structures, developments in space sciences, space processing and manufacturing, space operations, and applications of space technologies to other fields.

In most previous work at NASA Ames Research Center, ablation predictions for carbonaceous materials were obtained using a species thermodynamics database developed by Aerotherm Corporation. This database is derived mostly from the JANAF thermochemical tables. However, the CEA thermodynamics database, also used by NASA, is considered more up to date. In this work, the FIAT code was modified to use CEA-based curve fits for species thermodynamics, then analyses using both the JANAF and CEA thermodynamics were performed for carbon and carbon phenolic materials over a range of test conditions. The ablation predictions are comparable at lower heat fluxes where the dominant mechanism is carbon oxidation. However, the predictions begin to diverge in the sublimation regime, with the CEA model predicting lower recession. The disagreement is more significant for carbon phenolic than for carbon, and this difference is attributed to hydrocarbon species that may contribute to the ablation rate.