DIY liquid rocket engine - static fire qualification test campaign 2020 - ONE|AEROSPACE

[@manz5945]

Really cool work! And these Mach diamonds looks awesome!

[@oneaerospace8022]

Thank you!

[@CanineDefenseTechnologies]

This is some legit propulsion research!!

[@buraqaerospace9945]

You again first 😡😡😡😡

[@oneaerospace8022]

Thank you! We try to do everything as thoroughly as possible to reach good and safe results.

[@vishalk4647]

Woah aerospace club here.

[@gergelytolgyesi7326]

Those shock diamonds were actually pretty good looking ones

[@oneaerospace8022]

Indeed! Even though they are very small they turned out quite nice.

[@notmadrocketscientist1902]

Great work! Nice to see info about pressures and O/F ratio.

[@oneaerospace8022]

Thank you! Glad to hear that you like our work.

[@notbeast3494]

Test 16 you got super sonic Pretty awesome

[@quaesitumspatium7751]

What material do you plan on making the nozzle out of? Also the mach diamonds on 31 are gorgeous!

[@oneaerospace8022]

They are! Even though underexpanded flow is not very desireable at sea level in terms of thrust and Isp, we defenitely wanted to push the engine all the way up to design pressure before adding the diverging part of the nozzle to get thouse shots. In #33 and #34 the nozzle has already been added to the engine. However, due to the relatively low chamber pressure of only 6 bars it very small and therfore is hardly visible. The total axial length of the diverging nozzle is just a few millimeters.

[@quaesitumspatium7751]

@@oneaerospace8022 ah yes, I missed that it was added. You can really see the improvement with the expansion through the partial disappearance of the Mach diamonds.

[@NREYTERYREYTY5fddffsfdf]

Me: comparing Mach diamonds Them: getting data Data:

[@arnavkumar3060]

It produces shock diamonds 😍😍😍

[@jhhn369]

Thanks for being clear with your specs!

[@FijiWater1227]

What type of injector is it? It would be great if you can post cad files for the injector

[@dossaddict]

love the mach diamonds on 31

[@Zaku186]

i love the tiny mach diamonds

[@oneaerospace8022]

Difficult to see sometimes, but they are definitely pretty.

[@ok-hd4so]

the fuel igniting looks badass

[@cooperlane7147]

This is extremely impressive! How do you go about machining the nozzle?

[@oneaerospace8022]

Thank you! We have added the nozzle prior to the last two test firings in the video. However, due to the relatively small chamber pressures the nozzle is quite short and not clearly visible on the outside of the engine.

[@hadesaerospace5072]

do you plan to implement a TVC on this thruster once inserted into the rocket's fuselage?

[@oneaerospace8022]

Yes! We tought about more simple stabilization methods but due to the very low thrust to weight ratio of this engine type TVC seems to be the best way to go. We have built a first TVC mount with actuators (no tuned PID control so far) and we plan on testing it in combination with our second iteration engine after it has sucessfully been fired for the first time in the next week or so.

[@vertex3243]

@@oneaerospace8022is there going to be a new video soon?

[@oneaerospace8022]

Yes! We have tested the new engine version at very low mass flow rates but wanted to make some modifications before continuing. The engine should be ready by the end of this week. So hopefully we can continue testing as early as next week. Then we can finally upload some new videos

[@yeetman9k867]

2 things, I love your engine and I would like to suggest you do research on RP-1. RP-1 is kerosene and you can use it with Gox. And secondly, I was wondering how you pumped Gox to the combustion chamber because I'm also making a rocket engine. Thanks

[@oneaerospace8022]

Thank you! Well, we put a lot of thoughts into the fuel combination for our engine. Using some form of kerosene and GOx would definitely increase the Isp compared to ethanol/GOx. However, the combustion temperature and the mixture ratio would increase significatnly. As we currently have no active cooling this would lead to shorter burn times and much more GOx mass flow which is difficult to achieve with our current plumbing design (high gas velocities and pressure losses etc.). So for now ethanol works well for us but we will definitely think about it for future projects. And regarding the second part: The oxygen is stored in a gas cylinder under high pressure. So once we open the valves gas flow to the engine will automatically start due to the pressure drop.

[@danamulter]

Have you considered a NaK/Peroxide sea level engine stage? It's technically still "liquid"@@oneaerospace8022

[@kapytanhook]

So much chamber pressure, such nice mach diamonds but ISP of under 140. Makes the 400isp engines oit there seem even more impressive

[@oneaerospace8022]

They defenitely are! However, we can only reach very low chamber pressures of upt to 6.5 bar due to the pressure fed design approach. Thus, Isp is also very limited

[@melplishka5978]

You got Mach diamonds happenin.

[@doalgodoo5832]

Awesome! how much does the engine weigh when removed from the supporting plate?

[@holdenleeb2312]

I will watch your career with great interest

[@oneaerospace8022]

We are glad you like our content! We´ve made some significant changes to our engine over the past few weeks which will be tested very soon. Stay tuned!

[@Madsabre]

Great job!

[@oneaerospace8022]

Thank you!

[@fullflowaerospace]

nice!

[@PauloDutra]

Nice progress! Keep going!

[@oneaerospace8022]

Thank you! We will so stay tuned ;)

[@stormchaserjacobcook]

Great work!!!

[@oneaerospace8022]

Thanks!

[@tirthvora5061]

You will succeed!👍👍👍

[@oneaerospace8022]

Thank you! We will try our best!

[@MiguelAngel-bf4tc]

Oigan que combustible tienes

[@tomprivat9325]

Cool

[@buraqaerospace9945]

This was awesome

[@oneaerospace8022]

Thanks!

[@stephonhaydes2166]

I think test #31 was the most efficient....

[@orbitalalpha9442]

How do you make the combustion chamber and nozzle?

[@theredstonehive]

Nice mach diamonds

[@harleygreene1345]

Sporadic ignition source

[@sanskarraikar1095]

is the engine capable enough to launch the rocket coz even the engine must be heavy also great video

[@oneaerospace8022]

No, this is just an experimental version with changeable parts. We used this one to test basics such as injector and nozzle design, combustion stability, fuel ratios and the accuracy of our calculations. Due to the changeable nozzle design it is very heavy. However, from the results of the test campaign we were able to develope a fully redesigned engine with significantly reduced mass and higher pressure/thrust. This one will be tested for the first time hopefully by the end of this week and integrated into the rocket after succesful qualification.

[@sanskarraikar1095]

@@oneaerospace8022 thats sounds awesome all the best for the next test and I hope this gets successful

[@chasd00]

what is the injector design?

[@oneaerospace8022]

We use a coaxial swirl injector.

[@DawsonsMemes]

Rocket time

[@bulletslime5704]

nice

[@oneaerospace8022]

Thanks!

[@bigr3578]

Where'd you get the oxidizer from?

[@jpthepug3126]

It’s just liquid oxygen I’m sure

[@oneaerospace8022]

We use gaseous oxygen from our local hardware store

[@jonahosterried7832]

What has your fuel Flow been?

[@oneaerospace8022]

Fuel flow is given as total mass flow before every test in the video. Max was about 11 g/s

[@morningstar7009]

The nozzle literally squirt though

[@sonha6077]

Do rocket engine

[@NekoAerospaceSFS]

DIY SRB

[@oneaerospace8022]

Why SRB?