Launch Vehicle Propellant Usage[1]
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Apollo 11 |
Apollo 11 |
Apollo 11 |
Apollo 11 |
Apollo 12 |
Apollo 12 |
Apollo 12 |
Apollo 12 |
Apollo 13 |
Apollo 13 |
Apollo 13 |
Apollo 13 |
Apollo 14 |
Apollo 14 |
Apollo 14 |
Apollo 14 |
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Burn Start |
Burn End |
Burn Time |
Burn Rate Lb/Sec |
Burn Start |
Burn End |
Burn Time |
Burn Rate Lb/Sec |
Burn Start |
Burn End |
Burn Time |
Burn Rate Lb/Sec |
Burn Start |
Burn End |
Burn Time |
Burn Rate Lb/Sec |
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S-IC Burn (sec) |
-6.4 |
161.63 |
168.03 |
--- |
-6.5 |
161.74 |
168.24 |
--- |
-6.7 |
163.60 |
170.30 |
--- |
-6.5 |
164.10 |
170.60 |
--- |
Oxidizer (LOX), lb |
3,305,786 |
39,772 |
3,266,014 |
19,437.1 |
3,310,199 |
42,093 |
3,268,106 |
19,425.3 |
3,304,734 |
38,921 |
3,265,813 |
19,176.8 |
3,312,769 |
42,570 |
3,270,199 |
19,168.8 |
Fuel (RP-1), lb |
1,424,889 |
30,763 |
1,394,126 |
8,296.9 |
1,424,287 |
36,309 |
1,387,978 |
8,250.0 |
1,431,384 |
27,573 |
1,403,811 |
8,243.2 |
1,428,561 |
32,312 |
1,396,249 |
8,184.3 |
Total, lb |
4,730,675 |
70,535 |
4,660,140 |
27,734.0 |
4,734,486 |
78,402 |
4,656,084 |
27,675.2 |
4,736,118 |
66,494 |
4,669,624 |
27,420.0 |
4,741,330 |
74,882 |
4,666,448 |
27,353.2 |
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S-II Burn (sec) |
164.00 |
548.22 |
384.22 |
--- |
163.20 |
552.34 |
389.14 |
--- |
166.00 |
592.64 |
426.64 |
--- |
166.50 |
559.05 |
392.55 |
--- |
Oxidizer (LOX), lb |
819,050 |
3,536 |
815,514 |
2,122.5 |
825,406 |
3,536 |
821,870 |
2,112.0 |
836,741 |
3,533 |
833,208 |
1,953.0 |
837,484 |
2,949 |
834,535 |
2,125.9 |
Fuel (LH2), lb |
158,116 |
10,818 |
147,298 |
383.4 |
157,986 |
4,610 |
153,376 |
394.1 |
159,931 |
4,532 |
155,399 |
364.2 |
159,232 |
3,232 |
156,000 |
397.4 |
Total, lb |
977,166 |
14,354 |
962,812 |
2,505.9 |
983,392 |
8,146 |
975,246 |
2,506.2 |
996,672 |
8,065 |
988,607 |
2,317.2 |
996,716 |
6,181 |
990,535 |
2,523.3 |
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S-IVB 1st Burn (sec) |
552.20 |
699.33 |
147.13 |
--- |
556.60 |
693.91 |
137.31 |
--- |
596.90 |
749.83 |
152.93 |
--- |
563.40 |
700.56 |
137.16 |
--- |
Oxidizer (LOX), lb |
192,497 |
135,144 |
57,353 |
389.8 |
190,587 |
135,909 |
54,678 |
398.2 |
191,890 |
132,768 |
59,122 |
386.6 |
190,473 |
136,815 |
53,658 |
391.2 |
Fuel (LH2), lb |
43,608 |
31,736 |
11,872 |
80.7 |
43,663 |
32,346 |
11,317 |
82.4 |
43,657 |
31,455 |
12,202 |
79.8 |
43,546 |
32,605 |
10,941 |
79.8 |
Total, lb |
236,105 |
166,880 |
69,225 |
470.5 |
234,250 |
168,255 |
65,995 |
480.6 |
235,547 |
164,223 |
71,324 |
466.4 |
234,019 |
169,420 |
64,599 |
471.0 |
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S-IVB 2nd Burn (sec) |
9,856.20 |
10,203.03 |
346.83 |
--- |
10,042.80 |
10,383.94 |
341.14 |
--- |
9,346.30 |
9,697.15 |
350.85 |
--- |
8,912.40 |
9,263.24 |
350.84 |
--- |
Oxidizer (LOX), lb |
134,817 |
5,350 |
129,467 |
373.3 |
135,617 |
4,659 |
130,958 |
383.9 |
132,525 |
3,832 |
128,693 |
366.8 |
136,551 |
5,812 |
130,739 |
372.6 |
Fuel (LH2), lb |
29,324 |
2,112 |
27,212 |
78.5 |
29,804 |
2,109 |
27,695 |
81.2 |
29,367 |
1,963 |
27,404 |
78.1 |
30,428 |
2,672 |
27,756 |
79.1 |
Total, lb |
164,141 |
7,462 |
156,679 |
451.7 |
165,421 |
6,768 |
158,653 |
465.1 |
161,892 |
5,795 |
156,097 |
444.9 |
166,979 |
8,484 |
158,495 |
451.8 |
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Oxidizer-Fuel Ratio |
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S-IC Stage |
2.320 |
--- |
2.343 |
--- |
2.324 |
--- |
2.355 |
--- |
2.309 |
--- |
2.326 |
--- |
2.319 |
--- |
2.342 |
--- |
S-II Stage |
5.180 |
--- |
5.536 |
--- |
5.225 |
--- |
5.359 |
--- |
5.232 |
--- |
5.362 |
--- |
5.260 |
--- |
5.350 |
--- |
S-IVB Stage 1st burn |
4.414 |
--- |
4.831 |
--- |
4.365 |
--- |
4.831 |
--- |
4.395 |
--- |
4.845 |
--- |
4.374 |
--- |
4.904 |
--- |
S-IVB Stage 2nd burn |
4.597 |
--- |
4.758 |
--- |
4.550 |
--- |
4.729 |
--- |
4.513 |
--- |
4.696 |
--- |
4.488 |
--- |
4.710 |
--- |
[1]All times are referenced to Range Zero; all other values represent actual usage, in pounds mass. Sources are the Saturn V launch vehicle flight evaluation reports.