Launch Vehicle Propellant Usage[1]

 

 

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

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

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

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

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

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

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

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

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

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

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

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Oxidizer-Fuel Ratio

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

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.

 

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