I watched the time carefully, and noted the burn
lasted from about 37 seconds into the video until minute 1.07.
30 seconds in all. Any disagree.
So a 1/2 minute burn successfully accomplished.
Well done. Wunderbar!
So Copenhagen suborbital now has proven a rocket motor capable of
sending a sounding rocket upto 30 km.
Or perhaps upto 100 km.
Copenhagen Suborbital has shown remarkable success for a small
private group. Even a previous partial success for a sounding rocket launch
reaching ONLY eight kilometers altitude is remarkable, considering
that is the cruising altitude of many commercial jets.
The pipes down the left side are missing?
What was the reason for this change?
On the first test there was a heat exchanger that took the N2 around the nozzle and up to the tanks. But this time the tanks was pressurized with helium prior to the ignition.
TM65 from the first test. Photo Thomas Pedersen/CSThere was also put in an extra set of smaller valves for the pre-stage, where as in the first test the main valves was just opened to the tanks, that at this time was under low pressure, before open up for the N2 pressurized gas to the tanks in main stage.
This could not be done this time as the tanks already at 20 bar, so smaller valves was used instead.
Thanks for that very interesting.
I found a video on the CS webpage that said it was a helium heat exchanger but they were moving to N2 as it's cheaper.
So I'm confused and guessing maybe you got mixed up here?
On the first test there was a heat exchanger that took the N2 around the nozzle and up to the tanks. But this time the tanks was pressurized with helium prior to the ignition.
Thanks for that very interesting.
I found a video on the CS webpage that said it was a helium heat exchanger but they were moving to N2 as it's cheaper.
So I'm confused and guessing maybe you got mixed up here?
On the first test there was a heat exchanger that took the N2 around the nozzle and up to the tanks. But this time the tanks was pressurized with helium prior to the ignition.
True that they in the video said it was for helium, but the first test they did they ended up trying N2.
Here is the read out from the first test, where you can see the nitrogen gauge
Found an old blog where Peter Madsen, explain the changes that would be made from the first to the second test. Mainly the change to a pressure blow down system.
Next step TM65, now with 125% thrust.
Thanks very much, clears up the confusion
From what I've read if the data pans out......4 more of these engines will be built to power the next launcher.
It is not decided yet. The plan is to build and test a big engine, to see if that is the way to go. So time will tell if the big launcher will have 4 small or one big engine.
Maybe they still need to focus on the pressurization system to replace the expensive helium. They know the engine works; just need a less expensive pressure system.
From what I've read if the data pans out......4 more of these engines will be built to power the next launcher.
It is not decided yet. The plan is to build and test a big engine, to see if that is the way to go. So time will tell if the big launcher will have 4 small or one big engine.
Maybe they still need to focus on the pressurization system to replace the expensive helium. They know the engine works; just need a less expensive pressure system.
Well they are looking into turbopumps so we will most likely see a TM65 engine test with a pump in the future, but I imagine we have to wait at least to late 2013 (But then again CS have surprised me before, and I did get a picture of a pump lying on the floor at their workshop this Saturday). At the moment the engine use a pressure blow down system, and most likely the flight version of the TM65 too, that is planed for 2013.
Things can move fast in CS at times, and the development is not always linear, as there is more projects going on at the same time (not only in the engine department). It is the result of these project that will determine the direction they end up take.
From what I've read if the data pans out......4 more of these engines will be built to power the next launcher.
It is not decided yet. The plan is to build and test a big engine, to see if that is the way to go. So time will tell if the big launcher will have 4 small or one big engine.
Maybe they still need to focus on the pressurization system to replace the expensive helium. They know the engine works; just need a less expensive pressure system.
Well they are looking into turbopumps so we will most likely see a TM65 engine test with a pump in the future, but I imagine we have to wait at least to late 2013 (But then again CS have surprised me before, and I did get a picture of a pump lying on the floor at their workshop this Saturday). At the moment the engine use a pressure blow down system, and most likely the flight version of the TM65 too, that is planed for 2013.
Things can move fast in CS at times, and the development is not always linear, as there is more projects going on at the same time (not only in the engine department). It is the result of these project that will determine the direction they end up take.
yes, saw that about a turbo pump in a blog.
The team is good and gets alot done, so don't change a good thing.
Official CS video of the Saturday test
Camera 1 view
Perfectly stunning TM65-burn!We still have not seen TM65-engine full potential. In today's test we reached 9.5 bar, and Tordenskjold is designed to run at 12 and could handle 15
We had 18.7 bar LOX and 19.2 bar on fuel, so it was close to the desired 20
It was a wonderful experience to see the 50 kN as we got this time.
TM65 is a little too conservatively designed, and if we are up on the 12 bars, we either run with unreasonably high tank pressure or drill the injector. We have seen it plenty of pressure drop across the injector and also running with the correct ratio between fuel and lox.
A new test is planed the December 30
Tordenskjold to rumble again on December 30Regards
Morten
All good news !
Looking forward to Dec. 30th.
Just a friendly reminder if you like what you see and wish to be part of this; its funding that makes it happen. They are still shy on their next major goals.
http://www.indiegogo.com/TychoDeepSpace2?c=homeEdit: test date
Another enjoyable video from our Copenhagen friends.
CS have just released a video of the TDS-I capsule that was tested in a LES experiment last summer. The video consist of a run through and test of the subsystems, the LES launch itself and some conclusions at the end of the video. Some of the footages have been seen else were, but this time put into a video telling the whole story. There is also talk about doing a final drop test of the capsule from an airplane in the spring of 2013, to validate the parachutes.
2012 have been a busy year for CS. Kristian von Bengtson have released this graphical overview of the year. A bit amazed myself of all the things they have done when it is put up like that. Certainly look forward to 2013 with another year of development and experiments.
Copenhagen Suborbitals 2012 in Review
The year will end with a static test of TM65 on the 30. December, where CS hope to get the engine up to its full potential. The setup will be the same as the last test, but this time the injector have been drilled up to get a bigger flow of the fuel into the combustion chamber.
Peter Madsen have released these numbers of the engine that going to be tested
We run tests on 30 Dec - and here is the data for the modified TM65.TM65 Tordenskjold in numbers
Engine type:
Pressure cycle, bi propellant liquid fuel rocket engine.
Propellants:
Oxydizer: LOX.
Fuel: 75 % vol PFA alkohol / 25 % water.
By mass:
Ethyl alkohol:63 %
Isopropylalkohol: 7 %
water: 30 %
O/F ratio: 1.3
Cooling:
Chamber, regenerative. Nozzle, regenerative plus liquid film.
15 % of fuel flow is directed to nozzle film colling via 2 x 7,3 mm orifices. The film is injected via 56 2,0 mm holes in converging section of the nozzle.
Injector:
Like on like impinging.
Fuel: 100 x 2.5 mm holes in 50 pairs.
Oxydizer:132 x 2.5 mm holes in 66 pairs.
Cooling Jacket:
Type: Annular.
Flowspeed: Nozzle: 5.4 m/sek. Chamber 2.5 m/sek
Specific length L*:
2.0 m
Nozzle throat area:
450 cm2
Nozzle exit area:
1963 cm2
Nozzle expansion ratio:
4.36
Chamber pressure at 100 % rated thrust:
12.0 bars
Nominal sea level thrust:
65 kN @ Cf 1.2
Nominal sea level ISP:
200 sek
Nominal vacuum ISP:
235 sek
Development have also started of a turbo pump for the TM65 engine, that will be tested later on.
TM65 Turbine Pump in numbers:
Type:
Centrifugal pump, powered by single stage impulse turbine.
LOX pump:
Rpm:
4300 rpm.
Inlet pressure:
2 bars.
Outlet pressure:
20 bars.
Flow:
20 kg / sec.
Power consumption
50 kw
Fuel pump:
Centrifugal pump, powered by single stage impulse turbine.
Rpm:
6200 rpm
Inlet pressure:
2 bars.
Outlet pressure:
20 bars.
Flow:
15 kg / sec.
Power consumption
50 kw
Gas gennerator:
Propellant:
H202 80 %
catalyst:
KMnO4 solid.
Propellant mass flow:
0.45 kg /sec.
Steam data:
Water / oxygen mixture at 275 C @ 25 bars.
Controler:
Electronic, measuring rpm and outlet pressure, controlling H202 flow.
Each of the two turbine and pump units have a gas generator
and the units at mounted back to back but rotates in opposite directions and at different speeds.
I am planning to go and see the static test, and get some pictures. Here is some pictures I took of the last test and a visit into HAB afterward.
PhotosMerry Christmas everyone.
The inside of TDS-1 looks pretty beat up...
Gotta love their cams and feed.
Some issues with cam three.....came up for a sec
