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Saturn IB

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Saturn IB
Missing image
Apmisc-KSC-66PC-232.jpg
The Saturn IB rocket for the AS-202 mission

Saturn IB rocket.
Stages 2
1 - S-IB Engines 8 * H-1
Thrust 1,500,000 lbf (6.7 MN)
Burn time ~150 seconds
Fuels RP-1/LOX
2 - S-IVB Engines 1 * J-2
Thrust 890 kN
(200,000 lbf)
(later 1,000 kN)
Burn time ~475 s
Fuels LH2/LOX
Two stage version
Payload to LEO 15,300 kg


The Saturn IB was an uprated verson of the Saturn I, which was the first manned launch vehicle that was not directly derived from an ICBM (though its tanks were derived from the Jupiter and Redstone tanks, and its first stage engines were Navaho derived). It was conceived in 1962 for use as the launch vehicle for Apollo Earth orbital (block 1) missions (manned and unmanned), the manned Skylab flights, and the Apollo-Soyuz Test Project. The final production run (such as Skylab launch vehicles) did not have alternating black and white tanks on the first stage.

The main payload of the Saturn IB was the Apollo Spacecraft.

The Saturn family of rockets consist of Saturn I, Saturn IB and Saturn V


Height: 224 ft (68.3 m) with Apollo spacecraft
Diameter: 21 ft 8 in (6.6 m)
Finspan: 18 ft (5.5 m)
Number of fins: 8
Number of stages:2
Parts: Stage 1 (S-Ib), Stage 2 (S-IVB), instrument unit, interstage adapter

Data for the Saturn IB

Parameter S-IB - 1st Stage S-IVB - 2nd Stage Instrument Unit Apollo Spacecraft
Height (m) 25.5 17.8 1.00 24
Diameter (m) 6.6 6.6 6.6 3.9
Gross mass (kg) 458,107 119,920 1,980 20,788
Empty mass (kg) 45,267 13,311 225 14,098
Engines Eight - H-1 One - J-2 - One SPS
Thrust (kN) 7,582 1,020 - 97.86
Isp (s) 288 421 - 314
Isp (kNĚs/kg) 2.82 4.13 - 3.08
Burn duration (s) 150 470 - 635
Propellant LOX/RP-1 LOX/LH2 - N2O4/UDMH




















Saturn IB Launch Events

Launch Event Time (s) Altitude (km) Range (km)
Ignition Command -3.02 . .
First Motion -0.19 . .
Liftoff 0.00 . .
Initiate Pitch Maneuver 10.0 . .
Initiate Roll Maneuver 10.0 . .
End Roll Maneuver 38.0 . .
Mach One 62.18 7.63 .
Max Q 75.5 12.16 .
Freeze Tilt 134.40 . .
Inboard Engine Cutoff 140.65 . .
Outboard Engine Cutoff 144.32 . .
Ullage Rockets Ignition 145.37 . .
S-IB / S-IVB Separation 145.59 . .
S-IVB Ignition 146.97 . .
Ullage Rocket Burnout 148.33 . .
Ullage Rocket Jettison 156.58 . .
Jettison LES 163.28 . .
Start Pitch Over 613.95 . .
S-IVB Cutoff 616.76 . .
Orbit Insertion 626.76 . .
Start S/C Sep Sequence 663.11 . .
Spacecraft Separation 728.31 . .
































S-IB stage


Missing image
Saturn_IB_1st_stage.jpg
Diagram of the S-IB first stage of the Saturn IB rocket.

The S-IB stage is an eight engine booster for Earth orbital missions. It is composed of nine propellant containers, eight fins, a thrust structure assembly, eight H-1 rocket engines, and many other components. The propellant containers consist of eight Redstone tanks (Four holding LOX and four holding RP-1.) clustered around a Jupiter rocket tank, which contains LOX. The four outboard engines can gimble, meaning they can be steered to properly guide the rocket. This requires a few more engine components.

Specifications:

Height: 83.6 ft (25.5 m)
Diameter: 21.7 ft (6.6 m)
Number of fins: 8
Finspan: 18 ft (5.5 m)
Engines: 8 H-1
Thrust: 1,600,000 lbf (7.1 MN)
Fuel: RP-1 (Refined kerosene) 41,000 US gal (155 m³)
Oxidizer: Liquid oxygen (LOX) 66,000 US gal (250 m³)
Burn time: 2.5 min
Burnout altitude: 42 miles (68 km)

H-1 engine

Missing image
H-1_rocket_engine_diagram.jpg
H-1 Saturn I and Saturn IB rocket engine.

The H-1 engine is a 200,000 lbf (890 kN) thrust LOX/RP-1 engine, used alone in the first stages of some Delta rockets and the Jupiter rocket. It is derived from the Navaho missile, and was simplified and improved for S-IB use. It is used in clusters on all S-IB rocket stages. Later it would be uprated to 205,000 lbf (912 kN) of thrust. The H-1 preceded the F-1 engine, which was used on the Saturn V rocket.

Fuel: RP-1 (refined kerosene)
Oxidizer: liquid oxygen (LOX)
Height: 8.5 ft (2.6 m)
Width: 5.5 ft (1.7 m)
Thrust: 200,000 lbf (890 kN)
Uprated thrust: 205,000 lbf (912 kN)
Fuel flowrate: 2092 US gal/min (132 L/s)
Oxidizer flowrate: 3330 US gal/min (210 L/s)
Oxidizer to fuel ratio: 2.23:1
Type: bipropellant standard
Nominal chamber pressure: 633 lbf/in² (4.4 MPa)
Inboard weight: 1780 lb (810 kg)
Outboard weight: 2020 lb (920 kg)
Expansion area ratio: 8:1

S-IVB stage

Missing image
Saturn_S-IB_SIV-B.jpg
Diagram of the S-IVB second stage of the Saturn IB.

[see ]

The S-IVB stage is identical to the Saturn V rocket third stage except for the interstage adapter. It is powered by a single J-2 engine, which can gimble. This stage has a "common bulkhead," meaning that one propellant tank is directly connected to the other, as if conjoined twins. This saves about ten tons of weight.

Height: 58.4 ft (17.8 m)
Diameter: 21.7 ft (6.6 m)
Number of fins: 0
Engines: 1 J-2
Thrust: 200,000 lbf (890 kN)
Fuel: Liquid hydrogen (LH2) 64,000 US gal (242 m³)
Oxidizer: Liquid oxygen (LOX) 20,000 US gal (76 m³)
Burn time: approx. 7 min
Burnout altitude (for Saturn IB): orbit

J-2 engine

Missing image
J-2_rocket_engine.jpg
J-2 rocket engine.

The J-2 rocket engine was the most powerful hydrogen-fueled engine ever built, until the development of the Space Shuttle main engines (SSME). It is designed to operate in space, and was built specifically for space exploration.

Fuel: Liquid hydrogen (LH2)
Oxidizer: Liquid oxygen (LOX)
Height: 11 ft 1 in (3.4 m)
Width: 6 ft 8.5 in (2.0 m)
Thrust: 195,000 to 225,000 lbf (870 to 1,000 kN), 200,000 lbf (890 kN) standard
Uprated thrust: 230,000 lbf (1,020 kN)
Fuel flowrate: 7960 US gal/min (502 L/s)
Oxidizer flowrate: 2490 US gal/min (157 L/s)
Fuel to oxidizer ratio: 5:1 standard
Type: Bipropellant ratio variable (Thrust is varied by changing the fuel to oxidizer ratio.)
Nominal chamber pressure: 632 lbf/in² (4.4 MPa)
Weight: 3480 lb (1,580 kg)
Expansion area ratio: 27.5:1

All Saturn IB Launches

All Saturn IB Launches from AS-201 through ASTP.
Enlarge
All Saturn IB Launches from AS-201 through ASTP.

Saturn IB Vehicles and Launches

Serial Number Mission Launch Date Notes
AS-201 AS-201 February 26, 1966 1st test flight. Sub-orbital Command/Service Module test.
AS-203 AS-203 July 5, 1966 2nd test flight. Test of SIV-B stage. Tracked 4-orbits.
AS-202 AS-202 August 25, 1966 3rd test flight. 2nd Sub-orbital Command/Service Module test.
AS-204 Apollo 5 January 22, 1968 Earth orbit test of Lunar Module. Launched on Apollo 1 rocket. 36 orbits.
AS-205 Apollo 7 October 11, 1968 Earth orbit test. Crew: Schirra, Eisle, Cunningham. 163-orbits.
AS-206 Skylab 2 May 25, 1973 First Skylab crew: Conrad, Kerwin, Weitz. 404-orbits.
AS-207 Skylab 3 July 28, 1973 Second Skylab crew: Bean, Garriott, Lousma. 838-orbits.
AS-208 Skylab 4 November 16, 1973 Third and final Skylab crew: Carr, Gibson, Pogue. 1,214-orbits
AS-209 Skylab Rescue 1973, 1974 Skylab Rescue Mission. Not flown.
AS-210 ASTP July 15, 1975 Apollo-Soyuz Test Project, Crew: Stafford, Slayton, Brand. 136-orbits.
AS-211 Unused
AS-212 Unused. Second stage, SIV-B, converted to Skylab space station.
AS-213 Only 1st stage built. Unused
AS-214 Only 1st stage built. Unused

Further reading

pl:Saturn IB

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