Launch Vehicle Propellant Usage[1]
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Apollo 15 |
Apollo 15 |
Apollo 15 |
Apollo 15 |
Apollo 16 |
Apollo 16 |
Apollo 16 |
Apollo 16 |
Apollo 17 |
Apollo 17 |
Apollo 17 |
Apollo 17 |
Program Totals |
Program Totals |
Program Totals |
Program Totals |
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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) |
-6.5 |
159.56 |
166.06 |
--- |
-6.7 |
161.78 |
168.48 |
--- |
-6.9 |
161.20 |
168.10 |
--- |
--- |
--- |
1,677.31 |
--- |
Oxidizer (LOX), lb |
3,312,030 |
31,135 |
3,280,895 |
19,757.3 |
3,311,226 |
34,028 |
3,277,198 |
19,451.6 |
3,314,388 |
36,479 |
3,277,909 |
19,499.8 |
32,903,196 |
396,885 |
32,506,311 |
19,380.1 |
Fuel (RP-1), lb |
1,410,798 |
27,142 |
1,383,656 |
8,332.3 |
1,439,894 |
31,601 |
1,408,293 |
8,358.8 |
1,431,921 |
26,305 |
1,405,616 |
8,361.8 |
14,204,300 |
309,554 |
13,894,746 |
8,284.0 |
Total, lb |
4,722,828 |
58,277 |
4,664,551 |
28,089.6 |
4,751,120 |
65,629 |
4,685,491 |
27,810.4 |
4,746,309 |
62,784 |
4,683,525 |
27,861.5 |
47,107,496 |
706,439 |
46,401,057 |
27,664.1 |
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S-II Burn (sec) |
163.00 |
549.06 |
386.06 |
--- |
165.20 |
559.54 |
394.34 |
--- |
164.60 |
559.66 |
395.06 |
--- |
--- |
--- |
3,895.51 |
--- |
Oxidizer (LOX), lb |
837,991 |
3,109 |
834,882 |
2,162.6 |
846,157 |
3,141 |
843,016 |
2,137.8 |
844,094 |
3,137 |
840,957 |
2,128.7 |
8,285,547 |
34,876 |
8,250,671 |
2,118.0 |
Fuel (LH2), lb |
158,966 |
4,022 |
154,944 |
401.3 |
160,551 |
2,884 |
157,667 |
399.8 |
160,451 |
3,024 |
157,427 |
398.5 |
1,587,344 |
45,639 |
1,541,705 |
395.8 |
Total, lb |
996,957 |
7,131 |
989,826 |
2,563.9 |
1,006,708 |
6,025 |
1,000,683 |
2,537.6 |
1,004,545 |
6,161 |
998,384 |
2,527.2 |
9,872,891 |
80,515 |
9,792,376 |
2,513.8 |
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S-IVB 1st Burn (sec) |
553.20 |
694.67 |
141.47 |
--- |
563.60 |
706.21 |
142.61 |
--- |
563.80 |
702.65 |
138.85 |
--- |
--- |
--- |
1,424.94 |
--- |
Oxidizer (LOX), lb |
195,788 |
140,293 |
55,495 |
392.3 |
195,372 |
138,937 |
56,435 |
395.7 |
195,636 |
140,047 |
55,589 |
400.4 |
1,926,858 |
1,359,437 |
567,421 |
398.2 |
Fuel (LH2), lb |
43,674 |
32,416 |
11,258 |
79.6 |
43,727 |
32,081 |
11,646 |
81.7 |
43,752 |
32,685 |
11,067 |
79.7 |
436,119 |
320,565 |
115,554 |
81.1 |
Total, lb |
239,462 |
172,709 |
66,753 |
471.9 |
239,099 |
171,018 |
68,081 |
477.4 |
239,388 |
172,732 |
66,656 |
480.1 |
2,362,977 |
1,680,002 |
682,975 |
479.3 |
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S-IVB 2nd Burn (sec) |
10,202.90 |
10,553.61 |
350.71 |
--- |
9,216.50 |
9,558.42 |
341.92 |
--- |
11,556.60 |
11,907.64 |
351.04 |
--- |
--- |
--- |
3,156.17 |
--- |
Oxidizer (LOX), lb |
139,665 |
4,273 |
135,392 |
386.1 |
138,532 |
3,869 |
134,663 |
393.8 |
139,879 |
4,219 |
135,660 |
386.5 |
1,356,020 |
154,650 |
1,201,370 |
380.6 |
Fuel (LH2), lb |
29,799 |
1,722 |
28,077 |
80.1 |
29,968 |
2,190 |
27,778 |
81.2 |
30,050 |
2,212 |
27,838 |
79.3 |
295,583 |
44,392 |
251,191 |
79.6 |
Total, lb |
169,464 |
5,995 |
163,469 |
466.1 |
168,500 |
6,059 |
162,441 |
475.1 |
169,929 |
6,431 |
163,498 |
465.8 |
1,651,603 |
199,042 |
1,452,561 |
460.2 |
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Oxidizer-Fuel Ratio |
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S-IC Stage |
2.348 |
--- |
2.371 |
--- |
2.300 |
--- |
2.327 |
--- |
2.315 |
--- |
2.332 |
--- |
2.316 |
--- |
2.339 |
--- |
S-II Stage |
5.272 |
--- |
5.388 |
--- |
5.270 |
--- |
5.347 |
--- |
5.261 |
--- |
5.342 |
--- |
5.220 |
--- |
5.352 |
--- |
S-IVB Stage 1st burn |
4.483 |
--- |
4.929 |
--- |
4.468 |
--- |
4.846 |
--- |
4.471 |
--- |
5.023 |
--- |
4.418 |
--- |
4.910 |
--- |
S-IVB Stage 2nd burn |
4.687 |
--- |
4.822 |
--- |
4.623 |
--- |
4.848 |
--- |
4.655 |
--- |
4.873 |
--- |
4.588 |
--- |
4.783 |
--- |
[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.