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@@nedredguy As Oliver mentioned at the end, we expect some fire in the next few months, but more on that in the next video coming up in a week or two! 😉
@@CivilDefenseEngineer Actually, this time, we will use nitrogen since it's cheaper, and from our testing, we didn't find any negative effects. To produce ungodly amounts of nitrogen onboard the rocket, we will use a liquid nitrogen evaporator/heat exchanger that we discussed in this video: th-cam.com/video/7ULg5N_FP0U/w-d-xo.html
Or you can likely get similar or higher torque on the new valve by using the planetary gearsets out of electric drills instead of that angle drive. Lighter & more compact that way!
@@arwenrosefall8081 We won't use a turbopump, just a liquid nitrogen evaporator/heat exchanger to preasurize the tanks. We talked about the system here: th-cam.com/video/7ULg5N_FP0U/w-d-xo.htmlfeature=shared
Thank you for watching! If you wish to support our rocket developments, you can become a supporter at www.copsub.com/support-us
To visit us, check out tour availability here: www.copsub.com/about-us/guided-tours/
Excited to see an engine-related update! Eager to see a test, hoping for this year. Sending as much support as possible from the USA!
@@gsmontag Much appreciated!
Consistent progress, well done! Looking forward to the next development. 🚀👨🏻🚀
@@JW20236 Thanks! Next update in a week or two.
cool
So cool. Keep it up!
@@nagjrcjasonbower Will do, thanks!
0:45 Why use a gearbox for the motor? Why not save the extra weight and use a motor with more torque?
Fingers crossed!
When can we expect a BPM-25 engine test?
@@nedredguy As Oliver mentioned at the end, we expect some fire in the next few months, but more on that in the next video coming up in a week or two! 😉
How do you pressurize your fuels so that they flow into your engines?
Helium. It's the best pressurant because it's inert, and light, which makes it a great working fluid. Only downside is it's expensive.
@@CivilDefenseEngineer Actually, this time, we will use nitrogen since it's cheaper, and from our testing, we didn't find any negative effects. To produce ungodly amounts of nitrogen onboard the rocket, we will use a liquid nitrogen evaporator/heat exchanger that we discussed in this video: th-cam.com/video/7ULg5N_FP0U/w-d-xo.html
If I wher you I woud try to use the old big valves to feed all 5 combustion cabers.
Yeah, but first, we need to test just a single engine, and that requires finer adjustment control.
@@CopenhagenSuborbitals Shure.
Just do V ports on the large ball valve and then you can stick with your tried & tested previous valve
Or you can likely get similar or higher torque on the new valve by using the planetary gearsets out of electric drills instead of that angle drive. Lighter & more compact that way!
Hi
Unless you're planning to have engine-out capability, a single-turbopump multi-chamber engine seems more reliable
@@arwenrosefall8081 We won't use a turbopump, just a liquid nitrogen evaporator/heat exchanger to preasurize the tanks. We talked about the system here: th-cam.com/video/7ULg5N_FP0U/w-d-xo.htmlfeature=shared
@@CopenhagenSuborbitals Ah, pressure fed, fair enough for a suborbital rocket, no need to overcomplicate it
@@CopenhagenSuborbitals What are the benefits of a LN2 heat exchanger vs a COPV gaseous pressurization system?
Second
Third
Edit: Dangit, someone snuck in there.
First