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The goal is to extend an imaging-based, full-field, temperature and strain mapping measurement technique to high-temperatures (1,200°C) for the application to hot-structure ground testing. Additionally, full-field imaging measurements produce two orders of magnitude more data points which can better capture the strain and temperature gradients to be used to validate the thermal-mechanical models of the hot-structures. Consequently, the resulting higher fidelity models can be used to improve the optimization of the design of hypersonic flight vehicles. State of the art strain and temperature techniques are point measurements, or line measurements in the case of fiber optics, and all have a much lower spatial resolution compared to this imaging-based technique. Not only do these traditional methods require physical contact with the test article, but the state of the art strain measurement techniques on Carbon Matrix Composites are limited to 950 °C. GOM has a system that can measure strain at elevated temperatures using Digital Image Correlation (greater than 1,200°C), but they cannot provide evidence that their system can simultaneously measure strain and temperature while also aligning the temperature data with the strain data—aligned data is the most detailed and useful form of data for the purpose of model validation. We aim to prove that full-field, strain and temperature can be measured simultaneously and the data aligned at elevated temperatures up to 1,200°C. This approach combines the method high-temp DIC to obtain full-field strain measurements with infrared thermography to obtain full-field temperature measurements. Other systems have only proved to work at low temperatures. Extending the capabilities of the system to high temperatures is non-trivial and we will address the highest priority technical challenges associated with doing so during the CIF. The following are key objectives of the research: 1)Quantify the effect on strain and temperature measurement uncertainty due to heat haze and show sufficient mitigation if necessary by testing in a purged endowment (N2) or mixing the turbulent local near-surface atmosphere with an air knife. 2)Qualify paints to be used for speckle pattern for the purpose of both high-temperature Digital Image correlation and also Infrared Thermography on C/C and C/Si Carbon Matrix Composites, and Inconel super alloy. This application is novel, but similar to an existing system. GOM has a solution that has proof of operation during low temperature testing and we would like to extend the capabilities to much higher temperatures, a regime where the above technical challenges appear to prohibit the use of Digital Image Correlation—except in a few special cases-- and the potential to significantly increase the uncertainties in the temperature measurements from Infrared Thermal Imaging. Additionally, this work is complementary to efforts in rocketry; Paul Gradl at MSFC has expressed interest in this capability for ground testing on hot-structures used on the SLS, such as the rocket engine nozzles and engine manifolds. If the key objectives are met, then we would combine the solutions from 1 and 2 to simultaneously test the system on actual test article, as opposed to a coupon, and quantify the measurement uncertainty, so that we could advertise our new testing abilities to customers who had previously requested the capability.
Extended strain and temperature measurement regime → Improved model validation→ Higher fidelity models → More optimized hot-structure design; New measurement capability at AFRC, attracts more customers while simultaneously increasing the quality of our test data for NASA, DoD, and industry
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