Except(s) from the paper “On the study of fuel storage in space and practical engineering concerns”
Since the purpose is increase the understanding of how fuels and tanks react in space, it is necessary to study the four primary fuel mixtures. These being Aerozine/NTO, UDM/NTO, Kerosene/Ox and H/Ox, especially the latter, as there are few 3 example of actual use. This is especially due to the boil off problems encountered, when the engines where first developed in 1955. Given just how good these hydrolox engines can be, its a primary objective to test, if these can be used effectively in some manner.
The final probe design had with two rings of 6 individual tanks. The tanks had an identical volume, but different weights. Some included extra features such as insulation, or active cooling. The first ring was dedicated to the three currently used fuels, and the second ring was dedicated towards different H/Ox setups.
The first probe failed during circulation for reason unknown, but several smaller explosions where detected prior to the probe crashing back down into the atmosphere. The second probe did manage to reach a safe orbit mostly intact, two tanks exploded during ascent or shortly after reaching orbit. The reason is still not understood.
One hour after reaching space, we took a first snapshot of all data, we measured the following data:
|Fuel||Type||Dry Mass||Wet Mass||Result (1h)|
|Kerosene/Ox||ServiceModule||1,3610kg||14,25kg||0,25% O2 lost|
|Kerosene/Ox||Default||0,3680kg||13,25kg||All O2 lost|
|Kerosene/Ox||BallonCryo||0,2072kg||13,10kg||1,24% O2 lost|
|Kerosene/Ox||Cryogenic||0,3831kg||13,27kg||1,00% O2 lost|
|H/Ox||Ballon||0,07615kg||4,396kg||Exploded in orbit|
|H/Ox||Ballon + Rad*||0,07615kg||4,396kg||No loss|
|H/Ox||Cryogenic||0,2896kg||4,609kg||11,32% H2 lost|
|H/Ox||Cryogenic + Rad*||0,2896kg||4,609kg||No loss|
|H/Ox||BallonCryo||0,1137kg||4,433kg||Exploded during ascent|
|H/Ox||ServiceModule||1,2570k||5,577kg||2,56% H2 lost
0,0?% O2 lost
Rad* = Large flat radiator linked directly to the relevant tank.