user manual

Amendment 79
3/30/70
TABLE 3.3-17
LOAD CALCULATION
APS PROPELLANT Fuel Oxldi_er
i. Full tank - Item K, Table 3.3-16 (Ib) 20"7_ 3315.9
12. Density of off-load tables at loading
temperature and pressure (lb/ft 3) N/A N/A
13. Propellant volume (divide item 1 by
item 2. (ft 3) N/A N/A
14. Measured density (from Table 3,3-19)
(ib/ft H) N/A N/A
5. Resulting full tank load (ib) 2071.1 3315.9
6. Off-load amount (ib) 49.0 75.0
7. Propellant required to fill RCS manifolds
(ib) 7,9 12.7
8. Propellant load (Ib) 2014.2 3228.2
DPS PROPELLANT
9. Full tank - item K1 Table 3.3-16 (Ib) 7140.6 11441.9
ll0. Density of off-load tables st loadin8
temperature end pressure (ib/ft 3) N/A N/A
iii. Propellant volume (divide Item 9 by Item
10 )(ft 3) N/A N/A
112. Measured density (from Table 3.3-19)
(Ib/ft 3) N/A N/A
13. Resulting full tank load (ib) 7140,6 11440.9
14. Off-load amount (ib) 57.0 90.0
15. Propellant load (ib) 7083.6
RCS PROPELLANT
P. V. Calculations Fue____l Oxidizer
Tank A Tank B Tank A Tank B
NOTE:
A. GSE Volume (In 3) 18.45 37.& 17.94 30.25
B. Initial lJlla_p Pr*-..ure
(PSIC) 33.7 33.a 34,9 34.6
C. Initial GSE Pre.sure
(PSlC) i.o o.5 o.o o.o
D, Final GSE - S/C Pressure
(PSIG) _ 26.2 32.1 30.4
E. Ullage Volume (in 3) - Solve _ 134 205 7 219.01
the following equation by
substitutin8 the values in
the indicated step|.
(D-C) (A)
Ullase Volume -
B-D
lTheae items will be completed only if 8 density 8ample Is not
made prior to loadin8. If 8 density nmple ia made prior to
loadin$, then the item- will be left blank.
NASA _ MSC
il 11 11 E li- L
3.3-60 SNA-8-D-O27(III)REV 2
L L L L_ L K L; L_ L_ L k_
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L,.
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