To match conditions similar to those expected from the high speed flight, a propane blowtorch will be used to heat small samples of different materials with different ablative coatings (see test matrix below) while a thermocouple will monitor the surface temperature of the materials. The mass and thickness of the samples will be measured before and after the test to determine the effectiveness of the ablative coating used. A test stand has been built to hold the propane blowtorch at a specific distance from the samples (which can be adjusted as necessary).
The tests will be performed in a secure environment (blast chamber) and the operators will wear respirators during the tests. This document from Apogee Components was used as inspiration for this test procedure. Apogee Newsletter
Materials Used:
Thermocouple Amplifier MAX31855 breakout board (MAX6675 upgrade): https://www.adafruit.com/product/269
K-type thermocouple: https://www.adafruit.com/product/270
Jumper wires
Safety Notes:
Below is the matrix for samples used in this thermal test. All samples measured ~2" x 2" (with thickness depending on the sample), and there are three samples for each combination (for three trials). Each sample is labeled by "series" (1-9) with a hyphen, followed by the number of the trial. (so the nomenclature is series-trial number, for example: 4-2)
1/4" phenolic sheet | Series 1 | |
5-Layer Fiberglass | 10-Layer Fiberglass | |
---|---|---|
Control (West Systems epoxy) | Series 2 | Series 3 |
West Systems + Phenolic microballoons | Series 4 | Series 5 |
West Systems + High temperature paint | Series 6 | Series 7 |
West Systems + Microballoons + paint | Series 8 | Series 9 |
Fiberglass Sample Preparation:
Below are some pictures of the test stand, thermocouple used, Serial Monitor showing that the thermocouple works, and the fiberglass samples used (before they were cut and ablative coating was added)
The first thermal test we conducted was on a single 5-layer control sample of fiberglass (using West Systems epoxy). The purpose of this test was simply to see what improvements needed to be made for the next test, during which more samples will be tested. Below are photos of the sample after the test, as well as a graph of temperature vs. time.
Test Details:
Observations:
Improvements for Next Time:
Below is a table showing the results of the thermal tests. Consult the test matrix above to see what each "series" corresponds to (for example, "Series 1" means 1/4" phenolic sheet). All samples measured 2" x 2" in area. For a more detailed spreadsheet, consult the attached Excel spreadsheet. (ATTACH SPREADSHEET) In the table below, since some samples have multiple layers of ablative coating, a key is used to denote the mass/thickness of each layer, followed by the total mass/thickness.
F = fiberglass
P = phenolic sheet
PM = phenolic microballoons
H = high-temperature paint
*Mass of sample measured after hole drilled (to attach sample to test stand) and after all ablative coatings have been added, which is why there is a discrepancy between the total mass and the sum of the masses of each layer. In some cases, the mass measures zero for the high-temperature paint because the scale was not accurate enough and the layer was thin.
Series 1 | Series 2 | Series 3 | Series 4 | Series 5 | Series 6 | Series 7 | Series 8 | Series 9 | |||||||||||||||||||
---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
Trial | 1 | 2 | 3 | 1 | 2 | 3 | 1 | 2 | 3 | 1 | 2 | 3 | 1 | 2 | 3 | 1 | 2 | 3 | 1 | 2 | 3 | 1 | 2 | 3 | 1 | 2 | 3 |
Initial mass* [oz] | P: 0.780 | P: 0.780 | P: 0.780 | F: 0.135 | F: 0.135 | F: 0.145 | F: 0.290 | F: 0.295 | F: 0.280 | F: 0.140 PM: 0.050 Total: 0.200 | F: 0.150 PM: 0.065 Total: 0.220 | F: 0.160 PM: 0.060 Total: 0.220 | F: 0.305 PM: 0.075 Total: 0.365 | F: 0.300 PM: 0.055 Total: 0.355 | F: 0.305 PM: 0.050 Total: 0.355 | F: 0.150 H: 0.000 Total: 0.145 | F: 0.130 H: 0.005 Total: 0.135 | F: 0.135 H: 0.000 Total: 0.140 | F: 0.295 H: 0.000 Total: 0.290 | F: 0.280 H: 0.000 Total: 0.280 | F: 0.305 H: 0.000 Total: 0.305 | F: 0.140 PM: 0.04 H: 0.000 Total: 0.180 | F: 0.140 PM: 0.045 H: 0.000 Total: 0.185 | F: 0.140 PM: 0.045 H: 0.000 Total: 0.185 | F: 0.270 PM: 0.035 H: 0.000 Total: 0.305 | F: 0.270 PM: 0.035 H: 0.000 Total: 0.310 | F: 0.285 PM: 0.035 H: 0.005 Total: 0.320 |
Initial average thickness [mm] | P: 6.20 | P: 6.15 | P: 6.13 | F: 1.02 | F: 1.01 | F: 1.04 | F: 2.05 | F: 2.00 | F: 1.95 | F: 0.99 PM: 0.7 Total: 1.69 | F: 0.96 PM: 0.76 Total: 1.72 | F: 1.08 PM: 0.62 Total: 1.70 | F: 2.13 PM: 0.70 Total: 2.83 | F: 2.13 PM: 0.54 Total: 2.67 | F: 2.05 PM: 0.56 Total: 2.61 | F: 1.09 H: 0.04 Total: 1.13 | F: 0.94 H: 0.08 Total: 1.02 | F: 0.91 H: 0.06 Total: 0.97 | F: 1.94 H: 0.10 Total: 2.03 | F: 1.84 H: 0.18 Total: 2.02 | F: 1.89 H: 0.19 Total: 2.08 | F: 0.85 PM: 0.42 H: 0.28 Total: 1.55 | F: 0.84 PM: 0.59 H: 0.31 Total: 1.75 | F: 0.80 PM: 0.53 H: 0.35 Total: 1.68 | F: 1.75 PM: 0.55 H: 0.25 Total: 2.55 | F: 1.75 PM: 0.53 H: 0.33 Total: 2.61 | F: 1.75 PM: 0.52 H: 0.35 Total: 2.62 |
Final mass [oz] | 0.785 | 0.115 | 0.285 | ||||||||||||||||||||||||
Final average thickness [mm] |
https://tfaws.nasa.gov/TFAWS12/Proceedings/Aerothermodynamics%20Course.pdf