Temperature, Heat Flux and Recession Sensing for Ablative Thermal Protection Systems

Award Information
Agency:
National Aeronautics and Space Administration
Amount:
$124,997.00
Program:
SBIR
Contract:
NNX12CD48P
Solitcitation Year:
2011
Solicitation Number:
N/A
Branch:
N/A
Award Year:
2012
Phase:
Phase I
Agency Tracking Number:
114137
Solicitation Topic Code:
X9.01
Small Business Information
Industrial Measurement Systems Inc.
IL, Aurora, IL, 60502-8604
Hubzone Owned:
N
Woman Owned:
N
Socially and Economically Disadvantaged:
N
Duns:
927258277
Principal Investigator
 Donald Yuhas
 Principal Investigator
 (630) 236-5901
 dyuhas@imsysinc.com
Business Contact
 Donald Yuhas
Title: Business Official
Phone: (630) 236-5901
Email: dyuhas@imsysinc.com
Research Institution
 Stub
Abstract
Although significant advances have been made in ground-based testing and simulations, it is still impossible to precisely replicate the diversity of in-flight conditions experienced by ablative thermal protection systems (TPS). This leads to uncertainty in the predictions of the magnitude and rate of TPS ablation. Because in-flight monitoring is difficult, the uncertainty in actual boundary conditions and models must be considered when designing a TPS. To reduce risk, designers must resort to trade-offs which often involve increasing heat shield mass. Direct ablator temperature, heat flux and recession measurements would allow engineers to reduce design uncertainty and improve modeling. These improvements will lead to decreased heat shield mass, enabling missions that are not otherwise feasible and directly increasing science payload and returns.Ultrasonic methods for real-time monitoring of ablator conditions including internal temperature distribution, heat flux and recession will be developed in this program. Internal localization methods of ultrasonic thermometry will be used to accurately measure temperature distribution to within close proximity of surface charring. Temperature compensation will be applied to ultrasonic thickness gauging techniques to estimate surface recession in real time. Heat flux can be extracted from the measured temperature distribution. Combined together, these ultrasonic techniques will form a sensor system capable of sensing and relating real-world ablator performance to computational models as well as qualifying ablator materials. When developed to maturation, such a sensor system even has applications for in-flight health monitoring.

* information listed above is at the time of submission.

Agency Micro-sites

US Flag An Official Website of the United States Government