OTRAG Rocket.pdf

ocket. They must be considered in the mass and this one does in other missiles.
While blowing the gas pressure in the fuel, creating a low shear (270 N initially, in 13
seconds to 135 N to low). But this is usable? The missile has no OTRAG adaptation to
zero gravity decreases Once the thrust begins Furanol with the kerosene mix and the next
stage can not be ignited. A staging must be done so long as the push still does not drop,
just before the end of firing of the outer levels.
The specific impulse
Kayser is a specific impulse of 2648 m / s on the ground and 2913 m / s in vacuum on.
These values would be for this combination of fuel a record. I have to compare the
performance once the engine RD-214 indicated the Kosmos booster rocket, which works
with the same mixture:
Parameter OTRAG engine RD-214
KN 730 kN thrust 50-50
Chamber pressure of 10-30 bar 43.6 bar
Final pressure 0.7-2 bar 0889
Combustion chamber / Final pressure 15 52.3
Specific impulse ground 2648 2255
vacuum specific impulse 2913 2590
CEA: theoretical pulse vacuum 2474 2739
CEA: theoretical ground pulse 2135 2541
Although the pressure drop and the RD-214 is much larger (52.3 to 1) instead of (15 to 1)
and the engine always operates at the optimum pressure, has the engine from the OTRAG
a higher specific impulse, so a higher quantity of energy burned kilos of fuel on . This is
the data for the mixture HDA / kerosene. The mixture of nitric acid / kerosene is a little
worse, but not much (about 30 m / s).
I have published by the NASA CEA program that allows you to calculate, among other
things, the theoretical performance of a rocket engine under given boundary conditions,
fed with data from the OTRAG and RD 213th As used in this program an idealized
rocket engine in which it eg There is no need for cooling, a real engine always worse than
these theoretical values. You can see that the RD213. It is a slightly better specific
impulse (difference 150 m / s) obtained in the simulation.
Start 2 nachtsWie is different here OTRAG the engine! It operates with a lower chamber
pressure and a higher nozzle opening pressure, and yet it has a higher specific impulse!
Yes, the specific impulse is even higher than for any engine that was ever built with this
fuel combination. Even upper level with a much higher expansion ratio have less value.
But these values are not verifiable with CEA.
They are also verifiable from the data of the engines. If a module such as a fuel mass of
1350 kg and kn given a boost of 25 knots, decreasing linearly to 15 has at a burn time of
120 seconds, then gives a specific impulse of almost exactly 1778 m / s. At the same
values you get when the published data on heights and payloads OTRAG test shots back