Launch Vehicle Propellant Usage[1]

 

 

 

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

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

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)

-6.5

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

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

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

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

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

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

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

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Oxidizer-Fuel Ratio

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

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.

 

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