Future space exploration missions foresee high-speed entries into planetary atmospheres. These latter imply extreme thermal conditions to which the space vehicle is exposed to, and require an appropriate thermal protection system (TPS). The interest of the scientific community in modelling and testing of materials that compose the TPS has hence greatly increased over the past few years. Since a complete set of material properties is not available in open literature, it is difficult to numerically rebuild experiments. The inter-code comparison exercise proposed by the AF/SNL/NASA Ablation Workshop aims to give a baseline platform for ablation code calibration, with a complete set of material and gas properties. SACRAM 1.0 is a one-dimensiona...
Ablative materials are used in heat shields of spacecrafts re-entering the atmosphere to protect the...
Protecting a spacecraft during atmospheric entry is one of highest risk factors that needs to be mit...
This study demonstrates that coupling of a material thermal response code and a flow solver with non...
In the frame of its activities NASA as defined a one dimensional test case for assessing the capabil...
Ablative thermal protection materials are a key technology for current and future space exploration ...
When a spacecraft traveling at orbital speeds enters a planetary atmosphere, shock waves and frictio...
The Fully Implicit Ablation and Thermal Response code, FIAT, simulates pyrolysis and ablation of the...
Charring ablators remain the premium choice for space exploration missions that involve atmospheric ...
Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/76855/1/AIAA-2008-3805-224.pd
The purpose of this paper is to introduce and describe a 2-D fully implicit numerical simulation too...
A new method to simulate ablative Thermal Protection System (TPS) behaviour during an atmospheric en...
Ablating thermal protection system (TPS) materials have been used in many reentering spacecraft and ...
A critical problem in the design of Thermal Protection Systems (TPS) for planetary probes and re-ent...
The development of a new methodology to estimate the ablative Thermal Protection System (TPS) behavi...
Charring ablative thermal protection system (TPS) has been commonly used to prevent the payload of a...
Ablative materials are used in heat shields of spacecrafts re-entering the atmosphere to protect the...
Protecting a spacecraft during atmospheric entry is one of highest risk factors that needs to be mit...
This study demonstrates that coupling of a material thermal response code and a flow solver with non...
In the frame of its activities NASA as defined a one dimensional test case for assessing the capabil...
Ablative thermal protection materials are a key technology for current and future space exploration ...
When a spacecraft traveling at orbital speeds enters a planetary atmosphere, shock waves and frictio...
The Fully Implicit Ablation and Thermal Response code, FIAT, simulates pyrolysis and ablation of the...
Charring ablators remain the premium choice for space exploration missions that involve atmospheric ...
Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/76855/1/AIAA-2008-3805-224.pd
The purpose of this paper is to introduce and describe a 2-D fully implicit numerical simulation too...
A new method to simulate ablative Thermal Protection System (TPS) behaviour during an atmospheric en...
Ablating thermal protection system (TPS) materials have been used in many reentering spacecraft and ...
A critical problem in the design of Thermal Protection Systems (TPS) for planetary probes and re-ent...
The development of a new methodology to estimate the ablative Thermal Protection System (TPS) behavi...
Charring ablative thermal protection system (TPS) has been commonly used to prevent the payload of a...
Ablative materials are used in heat shields of spacecrafts re-entering the atmosphere to protect the...
Protecting a spacecraft during atmospheric entry is one of highest risk factors that needs to be mit...
This study demonstrates that coupling of a material thermal response code and a flow solver with non...