Current developments in future planetary probe sensors for TPS

Details Current developments in future planetary probe sensors for TPS Current developments in future planetary probe sensors for TPS

Feb 2004

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2004esasp.544..249m&link_type=abstract

In: Proceedings of the International Workshop Planetary Probe Atmospheric Entry and Descent Trajectory Analysis and Science, 6-9

Computer Science

Performance

Planetary Entry Probes, Sensors

Scientific paper

In situ Thermal Protection System (TPS) sensors are required during reentry to provide traceability of TPS sizing tools, design, and material performance. Traceability will lead to risk reduction and decreased heat-shield mass on subsequent missions requiring atmospheric aerocapture or entry/reentry. Decreasing heatshield mass will enable certain missions that are not otherwise feasible and directly increase science payload and returns. We consider two flight measurements as essential to advancing the state of TPS traceability for material modeling and aerothermal simulation: heat flux and surface recession (for ablators). The heat flux gage is applicable to both ablators and non-ablators and is therefore the more generalized sensor concept of the two, with wider applicability to mission scenarios. This paper describes the development, from NASA's Technical Readiness Level (TRL) 3 to 6, of a microsensor capable of surface and in-depth temperature and heat flux measurements for heatshield materials appropriate to Titan, Neptune, and Mars reentry. Progress to adapt a previously flown surface recession sensor, Galileo's Analog Resistance Ablation Detector (ARAD), to appropriate advanced aerocapture ablators is also discussed. Demonstrating quantitative sensor operation and functionality under relevant ground test environments would achieve TRL 6, defined as prototype demonstration in a relevant space or ground environment.

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