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Static Tests
Performed on the electronic test stands Year 2007 |
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Static Tests
Performed on the electronic test stands Year 2007 |
| < Go to 2006 tests | Go to 2008 tests > |
| Excel File |
Thrust Curve |
Description |
Video |
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| 1-27-07A1 (click for spreadsheet) |
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38-240 Casing, Dextrose rcandy
Evidence that KN/DX rcandy works and can be used in my motors. Burn time is longer than with recrystallized KN/Sucrose. |
Video 1 meg, 3 seconds .mpg file |
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| 2-24-07C (click for spreadsheet analysis) |
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38-240 casing, Malt Extract/Dextrose propellant. Approximately 2:1 dextrose to malt extract, plus about 0.3% RIO
This made a sharp little burn, surprising, since the malt extract propellant would not burn at all unless a torch was held to it (see Video 0) and dextrose propellant burns more slowly than KN/sucrose. Why should the combination of two slow propellants be faster than a fast one? Beats me. But I'll do some more experiments to find out. |
Video 1 1 meg, 5 seconds, .wmv file Video 0 3 attempts 2 meg .wmv file, 14 seconds |
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| 2-24-07D |
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38-240 casing, Malt Extract/Dextrose propellant. Replication of 2-24-07C except that propellant
contains about equal proportions of dextrose and dry malt extract.
It was barely non-continuous at 1 atmosphere, and expected to
burn moderately in the motor casing.
Surprise! Burn is almost identical to the previous test. This propellant contains slightly more RIO than the previous motor, approximately 0.5% Next tests will be made without RIO, to eliminate this complicating factor. |
Video 900K 5 seconds .wmv file |
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| 2-27-07A |  | 38-240 casing, Malt Extract/Dextrose propellant. Replication of 2-24-07C except that propellant
contains more dry malt extract than dextrose, 3:1 ratio. Propellant is made with 21% malt extract, 7% dextrose, and 14% Karo syrup. Doped with 0.01% (0.2g in whole 170gram batch) red iron oxide, it is a non-continuous burn, "chuffy" under propane-torch flame. 3-3/4 inch long fuse-paper ignitor used, extending full length of propellant grain.
Ignitor is expelled immediately upon ignition, followed by an ignition delay of about 2 seconds, but then by a quick ramp-up to full thrust and nominal burn thereafter. Burn time, pressure, and thrust are similar to KN/sucrose motors of this configuration. | Video 900K 5 seconds .wmv file | ||||||||||||||||||||||||
| 3-17-07B1 |
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38-240 Static test, Fuse Paper/Thermite ignitor.
Grain is uninhibited, very tight fit in case liner so no wrap of
fuse paper around grain this time. Ignitor is strip of rich fuse
paper 1.5 inches wide x 5.5 inches long. Last half of the roll is
spread with 0.2g RIO/Al mixture, 3:1 ratio. Ignitor secured with
full covering of green masking tape. Used new casting base and rod by Bob Gunar, made more precise grain, and the better-centered core may have contributed to the even burn.
Ignition quick, rise to pressure very fast, and thrust "curve" is amazingly flat. This bears replication. |
Video 1 meg 5 seconds .wmv file |
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| 3-17-07B2 |
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38-240 Static test, Fuse Paper/Thermite ignitor. Essentially the same as 3-17-07B1 but with slightly smaller grain.
Similar quick rise to pressure, not quite as clean a curve but quite acceptable. |
Video 1 meg 5 seconds .wmv file |
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| 3-18-07A |  | 38-240 static test, Fuse paper/thermite ignitor, RIO catalyzed propellant. Grain is made from same batch of propellant as used in both 3/17/07 tests, but 0.5% red iron oxide is added.
Burn is somewhat quicker, pressure and peak thrust considerably higher. Peak thrust on this test was about 1450 psi, peaks on the two 3/17 tests were 1000 and 1200 psi. | Video 1 meg 5 seconds .wmv file | ||||||||||||||||||||||||
| 3-18-07B (click for spreadsheet analysis) |  | 38-240 static test, fuse paper/thermite ignitor, Dry Malt Extract propellant.
Grain is made of remnant from3/9/07C, two parts dry malt extract,
1 part dextrose as primary fuels. This propellant does not
support its own combustion at 1 atmosphere, requires continual flame
source, and even then it chuffs.
Upon ignition, motor started slow burn. After about 6 seconds, it almost extinguished, then started chuffing. The chuffing continued to increase for about 6 seconds after which there was a strong thrust. Apparently the thermite ignitor does not ensure full igniton. Nor is it necessarily to be credited with the fast rise to pressure in the last 3 tests, as this one shows a fast rise once it gets past the chuffing, and by the time that had happened the ignitor was long gone. I'm going to name this propellant "Chuffmaster." | Video 2 meg 17 seconds .wmv file |