Engine Tests
On this page you will find the static and flight tests performed as well as their details.
V2 Engine - Test 2 - Static
Engine characteristics:
Propellant: KNSB
Nozzle: Nozzle 2
Burn characteristics:
Peak force: 124 N
Excel Data HERE.
Observations:
Nozzle:
- Fixed to the chamber with a circlip
Conclusion:
- The o-ring only burned on the part in contact with the combustion chamber
- Nozzle misaligned in relation to the combustion chamber
V2 Engine - Test 1 - Static
Engine characteristics:
Propellant: KNSB
Nozzle: Nozzle 1
Burn characteristics:
Peak force: 140 N
Excel Data HERE.
Observations:
Nozzle:
- Fixed to the chamber with a circlip
Conclusion:
- The o-ring burned
- Nozzle with high temperatures
V1 Engine - Test 9 - Flight
Engine characteristics:
Propellant: 65% potassium nitrate and 35% sorbitol
Nozzle: Nozzle 2
Observations:
Flight test of the V1 engine. No fuselage of any kind was used. We made use of a rod to ensure stability for the engine during flight. As for performance, we only obtained visual data. The rocket was not found. It probably went into orbit.
Date: 24-04-2021
V1 Engine - Test 8 - Static
Engine characteristics:
Propellant: 65% potassium nitrate and 35% sorbitol
Nozzle: Nozzle 2
Burn characteristics:
Maximum acceleration*: 219 m/s^2
Maximum theoretical ascent speed*: 144 m/s
Maximum theoretical descent speed*: 150 m/s
Maximum theoretical height*: 1147 m
* not considering the effects of aerodynamic resistance
Excel Data HERE.
Observations:
This was the last static test of the V1 Engine. We used a different fuel: sorbitol. The performance of the engine did not stand out relative to the others: apparently the performance got worse. Probably there were errors in the making of the propellant and its placement in the engine chamber.
Date: 24-04-2021
V1 Engine - Test 7 - Static
Engine characteristics:
Propellant: 65% potassium nitrate and 35% regular sugar
Nozzle: Nozzle 3
Burn characteristics:
Maximum acceleration*: 410 m/s^2
Maximum theoretical ascent speed*: 277 m/s
Maximum theoretical descent speed*: 283 m/s
Maximum theoretical height*: 4079 m
* not considering the effects of aerodynamic resistance
Excel Data HERE.
Observations:
This was the first test with the Type 3 nozzle. The peak force of the motor was much higher, but the burn time was shorter. The theoretical performance was much higher. Therefore, nozzle type 2 is not well designed. The initial peak also happened in this test because we did not change the ignition method yet. However, we did remove it again.
Date: 17-04-2021
V1 Engine - Test 6 - Static
Engine characteristics:
Propellant: 65% potassium nitrate and 35% regular sugar
Nozzle: Nozzle 2
Burn characteristics:
Maximum acceleration*: 220 m/s^2
Maximum theoretical ascent speed*: 149 m/s
Maximum theoretical descent speed*: 155 m/s
Maximum theoretical height*: 1219 m
* not considering the effects of aerodynamic resistance
Excel Data HERE.
Observations:
This test was exactly the same as Test 5 to see if the rockets were consistent and predictable or would perform differently. WE WERE SUCCESSFUL. VERY GOOD NEWS. The irregularities and the initial peak are still visible. As for the initial peak, it was again removed.
Date: 11-04-2021
V1 Engine - Test 5 - Static
Engine characteristics:
Propellant: 65% potassium nitrate and 35% regular sugar
Nozzle: Nozzle 2
Burn characteristics:
Maximum acceleration*: 208 m/s^2
Maximum theoretical ascent speed*: 154 m/s
Maximum theoretical descent speed*: 160 m/s
Maximum theoretical height*: 1299 m
* not considering the effects of aerodynamic resistance
Excel Data HERE.
Observations:
This was the second test with nozzle 2. The irregularities continue to register. The initial force peak is still there, as we continue with the same method for igniting the engine. However, as in the last test, we removed the initial peak force. The performance improved significantly due to the change in how we put the propellant into the combustion chamber and how we made the core. This change was eventually carried over to the following engines. The video of the burn is not complete due to problems with the filming.
Date: 11-04-2021
V1 Engine - Test 4 - Static
Engine characteristics:
Propellant: 65% potassium nitrate and 35% regular sugar
Nozzle: Nozzle 2
Burn characteristics:
Maximum acceleration*: 115 m/s^2
Maximum theoretical ascent speed*: 79 m/s
Maximum theoretical descent speed*: 88 m/s
Maximum theoretical height*: 391 m
* not considering the effects of aerodynamic resistance
Excel Data HERE.
Observations:
This was the first test with the steel nozzle. The performance was much lower, probably due to lack of precision in the measurements of nozzle 2 or the placement of the propellant. Irregularities are still being recorded. There was an abnormal initial force peak caused by the method used to ignite the engine. This force peak can be seen in the raw data. For a better approximation of reality, this peak has been removed from the graph.
Date: 01-04-2021
V1 Engine - Test 3 - Static
Engine characteristics:
Propellant: 65% potassium nitrate and 35% regular sugar
Nozzle: Nozzle 1
Burn characteristics:
Maximum acceleration*: 192 m/s^2
Maximum theoretical ascent speed*: 140 m/s
Maximum theoretical descent speed*: 146 m/s
Maximum theoretical height*: 1065 m
* not considering the effects of aerodynamic resistance
Excel Data HERE.
Observations:
This was the first engine to be tested on the test bench. For the first time we had the data on the force that the motor was generating. By capturing the force, we were able to detect some errors:
- The load cell, at the end of the firing, was left reading still considerable force values that can be seen in the raw data or even in the very slow force drop at the end. This was probably due to the friction between the motor and the support that holds it. For a better approximation of reality, these values were removed;
- An irregular graph. This could be from propellant breaking inside the chamber during firing, or from aluminum in the nozzle melting and causing anomalies;
Date: 07-03-2021
V1 Engine - Test 2 - Static
Engine characteristics:
Propellant: 65% potassium nitrate and 35% regular sugar
Nozzle: Nozzle 1
Observations:
This was the second V1 Engine. The nozzle was already attached by a screw to the engine chamber. At the time I did not yet have a test stand to measure the strength of the rocket.
V1 Engine - Test 1 - Static
Engine characteristics:
Propellant: 65% potassium nitrate and 35% regular sugar
Nozzle: Nozzle 1
Observations:
This was the first V1 Engine. The nozzle was not yet secured by a screw in the engine chamber. The nozzle could not withstand the pressures in the chamber, and was eventually ejected. At the time I didn’t yet have a test stand to measure the strength of the rocket, however, it gave good expectations!