A Case Study in NASA-DoD - The Black Vault

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Table E-l--Continued
I Unit Total Total
[ |Weight Weight |Cost
Item Quantity Size I Statusa I (lb) (lb) )
MMS-SPS-I, Propulsion Module, Hydrazine
Tanks Is P 10.2 10.2 20K
Thrusters 12 0.2 lb F P 0.6 7.2 144K
ValvesF
4 5 lb F P 1.25 5.0 48K
Drain and fill 2 P 0.25 0.5 4K
Isolation 4 P 0.7 2.8 20K
Miscellaneous
Press. regul.
Press. transd. 2 P 0.5 1.0 10K
Filters 2 P 0.25 0.5 4K
Plumbing 25 ft N 5.0 5K
Harness N 14.0
Structure N 2 9 . 0 h
Total dry weight, lb 75.2
Propellant weight, lb 55.0
Total wet weight, lb 130.2
MNS-SPS-1l, Propulsion Module, Hydrazine
Tanks 1 36" dia. PM 1 125.0 125.0 lOOK
x 55.5
cylindrical
Thrusters 12 0.2 lb_ P 0.6 7.2 144K
ValvesF
4 5 lb P 1.25 5.0 48K
Drain and fill 2 P 0.25 0.5 4K
Isolation 4 P 0.7 2.8 20K
Miscellaneous
Press. regul.
Press. transd. 2 P 0.5 1.0 1OK
Filters 2 P 0.25 0.5 4K
Plumbing 25 ft N 5.0 5K
Harness N 14.0
Structure N 8 1 . 0 h
Total dry weight, lb 242.0
Propellant weight, lb 1050.0
Total wet weight, lb 1292.0
an - flight-proven; PM - flight-proven but requires some modification;
N = new hardware.
bspin module cold gas system is same as three-axis except uses 8 thrusters
of 4 lbF each. which weigh and cost the same (0.5 lb/$5K each). System dry
weight is reduced by 2 lb.
cTRW estimates that $100-150K should be added to this value for integration
and test costs.
duses 2 end forgings from Viking Orbiter tank and existing elastomeric
diaphragm.
eFlight-qualified but have not flown.
fTRW estimates that $200-300K should be added to this value for integration
and test costs.
$SPS-I can employ 1, 2, 3, or 4 tanks providing propellant weights of 55,
110, 165, or 220 lb and corresponding system dry weights of 75, 87.2, 99.4, or
111.6 lb.
hIncludes propulsion module structure, drive electronics, remote interface
unit, GI2 and miscellaneous.
S 1 lxisting flight-qualifted tank developed for Viking Orbiter (VO-75) but
will replace surface tension expulsion device with an alastomaeric (AI-3-332)
* r bladder.