Add to ORKGSensors measure surface erosion rate of ablating material in reentry vehicle heat shield. Each sensor, which is placed at precise depths in the heat shield is activated when the ablator surface erodes to the location of a sensing point. Sensor depth and activation time determine ablator surface erosion rate
A heat shield for a space vehicle comprises a plurality of phenolic impregnated carbon ablator (PICA...
The development of a new sensor system for in-situ, real-time measurements of recession rate of heat...
This is a chart for the NASA Ames Instrumentation Workshop scheduled for 16-Sept-2015. The workshop ...
Design and development of sensors for measuring ablative changes in space vehicle heat shield during...
Design and operation of make wire, light pipe, and spring wire sensors to measure in-flight thermal ...
Radioactive isotope technique for heat shield ablation measurement during reentr
Reentry shielding ablation measured by imbedded radioactive isotopes with radiation decto
Design, operation and construction of event recorder for monitoring heat ablation dat
During all phases of a spacecraft's mission, a Thermal Protection System (TPS) is needed to protect ...
Results are presented from an investigation to determine the effects of fabrication-induced defects ...
Quantifying the thermal response of a heat shield is a key step in the design of a spacecraft to ens...
Radio frequency transmission characteristics of ablation materials for planetary entry vehicle heat ...
Hypersonic spacecraft reentering the earth's atmosphere encounter extreme heat due to atmospheric fr...
A spacecraft's thermal protection system (TPS) is required to survive the harsh environment experien...
Ablation behavior of heat shield of Apollo command module over wide range of thermal environment
A heat shield for a space vehicle comprises a plurality of phenolic impregnated carbon ablator (PICA...
The development of a new sensor system for in-situ, real-time measurements of recession rate of heat...
This is a chart for the NASA Ames Instrumentation Workshop scheduled for 16-Sept-2015. The workshop ...
Design and development of sensors for measuring ablative changes in space vehicle heat shield during...
Design and operation of make wire, light pipe, and spring wire sensors to measure in-flight thermal ...
Radioactive isotope technique for heat shield ablation measurement during reentr
Reentry shielding ablation measured by imbedded radioactive isotopes with radiation decto
Design, operation and construction of event recorder for monitoring heat ablation dat
During all phases of a spacecraft's mission, a Thermal Protection System (TPS) is needed to protect ...
Results are presented from an investigation to determine the effects of fabrication-induced defects ...
Quantifying the thermal response of a heat shield is a key step in the design of a spacecraft to ens...
Radio frequency transmission characteristics of ablation materials for planetary entry vehicle heat ...
Hypersonic spacecraft reentering the earth's atmosphere encounter extreme heat due to atmospheric fr...
A spacecraft's thermal protection system (TPS) is required to survive the harsh environment experien...
Ablation behavior of heat shield of Apollo command module over wide range of thermal environment
A heat shield for a space vehicle comprises a plurality of phenolic impregnated carbon ablator (PICA...
The development of a new sensor system for in-situ, real-time measurements of recession rate of heat...
This is a chart for the NASA Ames Instrumentation Workshop scheduled for 16-Sept-2015. The workshop ...
