Launch Vehicle/Spacecraft Key Facts

 

 

Apollo 7

Apollo 8

Apollo 9

Apollo 10

Apollo 11

Apollo 12

Apollo 13

Apollo 14

Apollo 15

Apollo 16

Apollo 17

 

 

 

 

 

 

 

 

 

 

 

 

First Stage (S-IB)

 

 

 

 

 

 

 

 

 

 

 

  Contractor

Chrysler

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  Diameter, base, ft

21.500

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---

---

---

---

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  Diameter, top, ft

21.667

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---

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---

---

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  Height, ft

80.200

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---

---

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---

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  Engines, type/number

H-1/8

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---

---

---

---

---

---

---

---

---

  Fuel

RP-1

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---

---

---

---

---

---

---

---

---

  Oxidizer

LO2

 

 

 

 

 

 

 

 

 

 

  Rated thrust each engine, lbf

200.000

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  Rated thrust total, lbf

1,600,000

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  Thrust at 35 to 38 sec, lbf

1,744,400

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First Stage (S-IC)

 

 

 

 

 

 

 

 

 

 

 

  Contractor

---

Boeing

Boeing

Boeing

Boeing

Boeing

Boeing

Boeing

Boeing

Boeing

Boeing

  Diameter, base, ft

---

33.000

33.000

33.000

33.000

33.000

33.000

33.000

33.000

33.000

33.000

  Diameter, top, ft

---

33.000

33.000

33.000

33.000

33.000

33.000

33.000

33.000

33.000

33.000

  Height, ft

---

138.030

138.030

138.030

138.030

138.030

138.030

138.030

138.030

138.030

138.030

  Engines, type/number

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F-1/5

F-1/5

F-1/5

F-1/5

F-1/5

F-1/5

F-1/5

F-1/5

F-1/5

F-1/5

  Fuel

---

RP-1

RP-1

RP-1

RP-1

RP-1

RP-1

RP-1

RP-1

RP-1

RP-1

  Oxidizer

---

LO2

LO2

LO2

LO2

LO2

LO2

LO2

LO2

LO2

LO2

  Rated thrust each engine, lbf

---

1,500,000

1,522,000

1,522,000

1,522,000

1,522,000

1,522,000

1,522,000

1,522,000

1,522,000

1,522,000

  Rated thrust total, lbf

---

7,500,000

7,610,000

7,610,000

7,610,000

7,610,000

7,610,000

7,610,000

7,610,000

7,610,000

7,610,000

  Thrust at 35 to 38 sec, lbf

---

7,560,000

7,576,000

7,536,000

7,552,000

7,594,000

7,560,000

7,504,000

7,558,000

7,620,000

7,599,000

 

 

 

 

 

 

 

 

 

 

 

 

Second Stage (S-II)

 

 

 

 

 

 

 

 

 

 

 

  Contractor

 

 

---

North American Rockwell

North American Rockwell

North American Rockwell

North American Rockwell

North American Rockwell

North American Rockwell

North American Rockwell

North American Rockwell

North American Rockwell

North American Rockwell

  Diameter, ft

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33.000

33.000

33.000

33.000

33.000

33.000

33.000

33.000

33.000

33.000

  Height, ft

---

81.500

81.500

81.500

81.500

81.500

81.500

81.500

81.500

81.500

81.500

  Engines, type/number

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J-2/5

J-2/5

J-2/5

J-2/5

J-2/5

J-2/5

J-2/5

J-2/5

J-2/5

J-2/5

  Fuel

---

LH2

LH2

LH2

LH2

LH2

LH2

LH2

LH2

LH2

LH2

  Oxidizer

---

LO2

LO2

LO2

LO2

LO2

LO2

LO2

LO2

LO2

LO2

  Rated thrust each engine, lbf

---

225,000

230,000

230,000

230,000

230,000

230,000

230,000

230,000

230,000

230,000

  Rated thrust total, lbf

---

1,125,000

1,150,000

1,150,000

1,150,000

1,150,000

1,150,000

1,150,000

1,150,000

1,150,000

1,150,000

  Thrust, engine start

     command +61 sec, lbf

 

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1,143,578

 

1,155,611

 

1,159,477

 

1,155,859

 

1,161,534

 

1,160,767

 

1,164,464

 

1,169,662

 

1,163,534

 

1,156,694

  Thrust, outboard engine

     cutoff, lbf

 

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865,302

 

730,000

 

642,068

 

625,751

 

611,266

 

635,725

 

580,478

 

548,783

 

787,380

 

787,009

 

Compiled from Saturn launch vehicle flight evaluation reports. Thrust for S-IC stage is at sea level and for the S-II and S-IVB stages is at altitude. Thrust listed at “35 to 38 sec”, “Engine Start Command + 61 seconds”, and at “Outboard Engine Cutoff” is actual thrust as flown.

 

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