Saturn IB: Difference between revisions

Saturn IB
	Three launch configurations of the Apollo Saturn IB rocket: no spacecraft (AS-203), command and service module (AS-202), and Lunar Module (Apollo 5)
Function	Apollo spacecraft development;; S-IVB stage development in support of Saturn V;; Skylab crew launcher
Manufacturer	Chrysler (S-IB); Douglas (S-IVB)
Country of origin	United States
Size
Height	141.6 ft (43.2 m); without payload
Diameter	21.67 ft (6.61 m)
Mass	1,300,220 lb (589,770 kg); without payload
Stages	2
Capacity
Payload to LEO
Altitude	87.5 nmi (162.1 km; 100.7 mi)
Mass	21,000 kg (46,000 lb)
Launch history
Status	Retired
Launch sites	Cape Canaveral, LC-34 and LC-37; Kennedy, LC-39B
Total launches	9
Success(es)	9
First flight	February 26, 1966
Last flight	July 15, 1975
Type of passengers/cargo	Apollo CSM,; Uncrewed Apollo LM
First stage – S-IB
Height	24.44 m (80.17 ft)
Diameter	6.53 m (21.42 ft)
Empty mass	42,000 kg (92,500 lb)
Gross mass	441,000 kg (973,000 lb)
Propellant mass	399,400 kg (880,500 lb)
Powered by	8 × H-1
Maximum thrust	7,100 kN (1,600,000 lbf)
Specific impulse	272 s (2.67 km/s)
Burn time	150 seconds
Propellant	LOX / RP-1
Second stage – S-IVB
Height	17.81 m (58.42 ft)
Diameter	6.53 m (21.42 ft)
Empty mass	10,600 kg (23,400 lb)
Gross mass	114,300 kg (251,900 lb)
Propellant mass	103,600 kg (228,500 lb)
Powered by	1 × J-2
Maximum thrust	890 kN (200,000 lbf)
Specific impulse	420 s (4.1 km/s)
Burn time	480 seconds
Propellant	LOX / LH2
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The Saturn IB^[a] (also known as the uprated Saturn I) was an American launch vehicle commissioned by the National Aeronautics and Space Administration (NASA) for the Apollo program. It uprated the Saturn I by replacing the S-IV second stage (90,000-pound-force (400,000 N), 43,380,000 lb-sec total impulse), with the S-IVB (200,000-pound-force (890,000 N), 96,000,000 lb-sec total impulse). The S-IB first stage also increased the S-I baseline's thrust from 1,500,000 pounds-force (6,700,000 N) to 1,600,000 pounds-force (7,100,000 N) and propellant load by 3.1%. This increased the Saturn I's low Earth orbit payload capability from 20,000 pounds (9,100 kg) to 46,000 pounds (21,000 kg), enough for early flight tests of a half-fueled Apollo command and service module (CSM) or a fully fueled Apollo Lunar Module (LM), before the larger Saturn V needed for lunar flight was ready.

By sharing the S-IVB upper stage, the Saturn IB and Saturn V provided a common interface to the Apollo spacecraft. The only major difference was that the S-IVB on the Saturn V burned only part of its propellant to achieve Earth orbit, so it could be restarted for trans-lunar injection. The S-IVB on the Saturn IB needed all of its propellant to achieve Earth orbit.

The Saturn IB launched two uncrewed CSM suborbital flights to a height of 162 km, one uncrewed LM orbital flight, and the first crewed CSM orbital mission (first planned as Apollo 1, later flown as Apollo 7). It also launched one orbital mission, AS-203, without a payload so the S-IVB would have residual liquid hydrogen fuel. This mission supported the design of the restartable version of the S-IVB used in the Saturn V, by observing the behavior of the liquid hydrogen in weightlessness.

In 1973, the year after the Apollo lunar program ended, three Apollo CSM/Saturn IBs ferried crews to the Skylab space station. In 1975, one last Apollo/Saturn IB launched the Apollo portion of the joint US-USSR Apollo–Soyuz Test Project (ASTP). A backup Apollo CSM/Saturn IB was assembled and made ready for a Skylab rescue mission, but never flown.

The remaining Saturn IBs in NASA's inventory were scrapped after the ASTP mission, as no use could be found for them and all heavy lift needs of the US space program could be serviced by the cheaper and more versatile Titan III family and also the Space Shuttle.

History

In 1959, NASA's Silverstein Committee issued recommendations to develop the Saturn class launch vehicles, growing from the C-1. When the Apollo program was started in 1961 with the goal of landing men on the Moon, NASA chose the Saturn I for Earth orbital test missions. However, the Saturn I's payload limit of 20,000 pounds (9,100 kg) to 162 km would allow testing of only the command module with a smaller propulsion module attached, as the command and service module would have a dry weight of at least 26,300 pounds (11,900 kg), in addition to service propulsion and reaction control fuel. In July 1962, NASA announced selection of the C-5 for the lunar landing mission, and decided to develop another launch vehicle by upgrading the Saturn I, replacing its S-IV second stage with the S-IVB, which would also be modified for use as the Saturn V third stage. The S-I first stage would also be upgraded to the S-IB by improving the thrust of its engines and removing some weight. The new Saturn IB, with a payload capability of at least 35,000 pounds (16,000 kg),^[4] would replace the Saturn I for Earth orbit testing, allowing the command and service module to be flown with a partial fuel load. It would also allow launching the 32,000-pound (15,000 kg) lunar excursion module separately for uncrewed and crewed Earth orbital testing, before the Saturn V was ready to be flown. It would also give early development to the third stage.^[2]

On May 12, 1966, NASA announced the vehicle would be called the "uprated Saturn I", at the same time the "lunar excursion module" was renamed the lunar module. However, the "uprated Saturn I" terminology was reverted to Saturn IB on December 2, 1967.^[2]

By the time it was developed, the Saturn IB payload capability had increased to 41,000 pounds (19,000 kg).^[2] By 1973, when it was used to launch three Skylab missions, the first-stage engine had been upgraded further, raising the payload capability to 46,000 pounds (21,000 kg).

Specifications

Launch vehicle

Parameter^[1]	S-IB (1st stage)	S-IVB (2nd stage)	Instrument unit
Height	24.44 m (80.17 ft)	17.81 m (58.42 ft)	0.91 m (3 ft)
Diameter	6.53 m (21.42 ft)	6.61 m (21.67 ft)	6.61 m (21.67 ft)
Structural mass	42,000 kg (92,500 lb)	10,600 kg (23,400 lb)	2,000 kg (4,400 lb)
Propellant	LOX / RP-1	LOX / LH₂	—
Propellant mass	399,400 kg (880,500 lb)	103,600 kg (228,500 lb)	—
Engines	8 × H-1	1 × J-2	—
Thrust	7,100 kN (1,600,000 lbf) sea level	890 kN (200,000 lbf) vacuum	—
Burn duration	150 seconds	480 seconds	—
Specific impulse	272 s (2.67 km/s) sea level	420 s (4.1 km/s) vacuum	—
Contractor	Chrysler	Douglas	IBM

Payload configurations

Parameter	Command and service module	Apollo 5	AS-203
Launch Escape System mass	4,200 kg (9,200 lb)	—	—
Apollo command and service module mass	16,500 to 20,900 kg (36,400 to 46,000 lb)	—	—
Apollo Lunar Module mass	—	14,360 kg (31,650 lb)	—
Spacecraft–LM adapter mass	1,840 kg (4,050 lb)	1,840 kg (4,050 lb)	—
Nose cone height	—	2.5 m (8.3 ft)	8.4 m (27.7 ft)
Payload height	24.9 m (81.8 ft)	11.1 m (36.3 ft)	—
Total space vehicle height	68.1 m (223.4 ft)	54.2 m (177.9 ft)	51.6 m (169.4 ft)

S-IB first stage

The S-IB stage was built by the Chrysler corporation at the Michoud Assembly Facility, New Orleans.^[5] It was powered by eight Rocketdyne H-1 rocket engines burning RP-1 fuel with liquid oxygen (LOX). Eight Redstone tanks (four holding fuel and four holding LOX) were clustered around a Jupiter rocket LOX tank, which earned the rocket the nickname "Cluster's Last Stand".^[6] The four outboard engines were mounted on gimbals, allowing them to be steered to control the rocket. Eight fins surrounding the base thrust structure provided aerodynamic stability and control.

Data from:^[7]

General characteristics

Length: 24.44 metres (80.17 ft)
Diameter: 6.53 metres (21.42 ft)
Wingspan: 12.02 metres (39.42 ft)

Engine

8 × Rocketdyne H-1
- Thrust: 7,100 kilonewtons (1,600,000 lbf)
- Burn time: 150 seconds
- Fuel: LOX / RP-1

S-IVB second stage

The S-IVB was built by the Douglas Aircraft Company at Huntington Beach, California. The S-IVB-200 model was similar to the S-IVB-500 third stage used on the Saturn V, with the exception of the interstage adapter, smaller auxiliary propulsion control modules, and lack of on-orbit engine restart capability. It was powered by a single Rocketdyne J-2 engine. The fuel and oxidizer tanks shared a common bulkhead, which saved about ten tons of weight and reduced vehicle length over ten feet.

General characteristics

Length: 17.81 metres (58.42 ft)
Diameter: 6.61 metres (21.67 ft)

Engine

1 × Rocketdyne J-2
- Thrust: 890 kilonewtons (200,000 lbf)
- Burn time: ~420 seconds
- Fuel: LOX / LH₂

Instrument unit

IBM built the instrument unit at the Space Systems Center in Huntsville, Alabama. Located at the top of the S-IVB stage, it consisted of a Launch Vehicle Digital Computer (LVDC), an inertial platform, accelerometers, a tracking, telemetry and command system and associated environmental controls. It controlled the entire rocket from just before liftoff until battery depletion. Like other rocket guidance systems, it maintained its state vector (position and velocity estimates) by integrating accelerometer measurements, sent firing and steering commands to the main engines and auxiliary thrusters, and fired the appropriate ordnance and solid rocket motors during staging and payload separation events.

As with other rockets, a completely independent and redundant range safety system could be invoked by ground radio command to terminate thrust and to destroy the vehicle should it malfunction and threaten people or property on the ground. In the Saturn IB and V, the range safety system was permanently disabled by ground command after safely reaching orbit. This was done to ensure that the S-IVB stage would not inadvertently rupture and create a cloud of debris in orbit that could endanger the crew of the Apollo CSM.

Launch sequence events

Launch event^[8]	Time (s)	Altitude (km)	Speed (m/s)
Guidance ref release	-5.0	0.09	0
First motion	0.0	0.09	0
Mach 1	58.9	7.4	183
Max dynamic pressure	73.6	12.4	328
Freeze tilt	130.5	48.2	1587
Inboard engine cutoff	137.6	54.8	1845
Outboard engine cutoff	140.6	57.6	1903
S-IB / S-IVB separation	142.0	59.0	1905
S-IVB ignition	143.4	59.9	1900
Ullage case jettison	154.0	69.7	1914
Launch escape tower jettison	165.6	79.5	1960
Iterative guidance mode initiation	171.0	83.7	1984
Engine mixture ratio shift	469.5	164.8	5064
Guidance C/O signal	581.9	158.4	7419
Orbit insertion	591.9	158.5	7426

Acceleration of the Saturn IB increased from 1.24 G at liftoff to a maximum of 4.35 G at the end of the S-IB stage burn, and increased again from 0 G to 2.85 G from stage separation to the end of the S-IVB burn.^[8]

AS-206, 207, and 208 inserted the Command and Service Module in a 150-by-222-kilometer (81-by-120-nautical-mile) elliptical orbit which was co-planar with the Skylab one. The SPS engine of the Command and Service Module was used at orbit apogee to achieve a Hohmann transfer to the Skylab orbit at 431 kilometers (233 nautical miles).^[8]

Saturn IB vehicles and launches

The first five Saturn IB launches for the Apollo program were made from LC-34 and LC-37, Cape Kennedy Air Force Station.

The Saturn IB was used between 1973 and 1975 for three crewed Skylab flights, and one Apollo-Soyuz Test Project flight. This final production run did not have alternating black and white S-IB stage tanks, or vertical stripes on the S-IVB aft tank skirt, which were present on the earlier vehicles. Since LC-34 and 37 were inactive by then, these launches utilized Kennedy Space Center's LC-39B.^[9] Mobile Launcher Platform No. 1 was modified, adding an elevated platform known as the "milkstool" to accommodate the height differential between the Saturn IB and the much larger Saturn V.^[9] This enabled alignment of the Launch Umbilical Tower's access arms to accommodate crew access, fueling, and ground electrical connections for the Apollo spacecraft and S-IVB upper stage. The tower's second stage access arms were modified to service the S-IB first stage.^[9]

Serial number	Launch date (UTC)	Launch site	Mission	Spacecraft mass (kg)	Notes
SA-201	February 26, 1966 16:12:01	Cape Kennedy, LC-34	AS-201	20,820	Uncrewed suborbital test of Block I CSM (command and service module)
SA-203	July 5, 1966 14:53:17	Cape Kennedy, LC-37B	AS-203	None	Uncrewed test of unburned LH₂ behavior in orbit to support S-IVB-500 restart design
SA-202	August 25, 1966 17:15:32	Cape Kennedy, LC-34	AS-202	25,810	Uncrewed suborbital test of Block I CSM
SA-204		Cape Kennedy, LC-34	Apollo 1	20,412	Was to be first crewed orbital test of Block I CSM. Cabin fire on January 27, 1967, killed astronauts and damaged CM during dress rehearsal for planned February 21, 1967 launch
SA-204	January 22, 1968 22:48:08	Cape Kennedy, LC-37B	Apollo 5	14,360	Uncrewed orbital test of lunar module, used Apollo 1 launch vehicle
SA-205	October 11, 1968 15:02:45	Cape Kennedy, LC-34	Apollo 7	16,520	Crewed orbital test of Block II CSM
SA-206	May 25, 1973 13:00:00	Kennedy, LC-39B	Skylab 2	19,979	Block II CSM ferried first crew to Skylab orbital workshop
SA-207	July 28, 1973 11:10:50	Kennedy, LC-39B	Skylab 3	20,121	Block II CSM ferried second crew to Skylab orbital workshop
SA-208		Kennedy, LC-39B	AS-208		Standby Skylab 3 rescue CSM-119; not needed
SA-208	November 16, 1973 14:01:23	Kennedy, LC-39B	Skylab 4	20,847	Block II CSM ferried third crew to Skylab orbital workshop
SA-209		Kennedy, LC-39B	AS-209		Standby Skylab 4 and later Apollo-Soyuz rescue CSM-119. Not needed, currently on display in the KSC rocket garden
SA-209			Skylab 5		Planned CSM mission to lift Skylab workshop's orbit to endure until Space Shuttle ready to fly; cancelled.
SA-210	July 15, 1975 19:50:01	Kennedy, LC-39B	ASTP	16,780	Apollo CSM with special docking adapter module, rendezvoused with Soyuz 19. Last Saturn IB flight.
SA-211					Unused. First stage was on display at the Alabama Welcome Center on I-65 in Ardmore, Alabama from 1979 to 2023: Now dismantled for disposal.^[10] S-IVB stage rests with Skylab underwater training simulator hardware and is on display outdoors at the U.S. Space and Rocket Center in Huntsville, Alabama.
SA-212					Unused. First stage scrapped.^[5] S-IVB stage converted to Skylab space station.
SA-213					Only first stage built. Unused and scrapped.^[5]
SA-214					Only first stage built. Unused and scrapped.^[5]

For earlier launches of vehicles in the Saturn I series, see the list in the Saturn I article.

Saturn IB rockets on display

As of 2023 there are two locations where Saturn IB vehicles (or parts thereof) are on display:

SA-209 is on display at the Kennedy Space Center Visitor Complex, with the Apollo Facilities Verification Vehicle. Due to severe corrosion, the first stage engines and service module were replaced with fabricated duplicates in 1993–1994.
The SA-211 S-IVB stage was mated with the Skylab underwater training docking adapter and Apollo Telescope Mount and is on display in the Rocket Garden of the U.S. Space & Rocket Center in Huntsville, Alabama. The SA-211 first stage was on display with a mockup S-IVB stage stacked in a launch-ready condition at the Alabama Welcome Center on Interstate 65 in Ardmore, Alabama, since July 1979.34°57′16″N 86°53′31″W / 34.954548°N 86.89193°W / 34.954548; -86.89193^[11]^[12] The structural integrity of the display, after four decades of weathering, could not be repaired. Dismantling of the vehicle for disposal began by September 14, 2023.^[10]

Cost

In 1972, the cost of a Saturn IB including launch was US$55,000,000 (equivalent to $401,000,000 in 2023).^[13]

Notes

^ Pronounced "saturn one bee"

References

^ ^a ^b ^c Postlaunch report for mission AS-201 (Apollo spacecraft 009) - (PDF), NASA, May 1966, retrieved March 18, 2011
^ ^a ^b ^c ^d Wade, Mark. "Saturn IB". Encyclopedia Astronautica. Archived from the original on May 14, 2011. Retrieved March 17, 2011.
^ Hornung, John (2013). Entering the Race to the Moon: Autobiography of an Apollo Rocket Scientist. Williamsburg, Virginia: Jack Be Nimble Publishing. ISBN 9780983044178.
^ Benson, Charles D.; Faherty, William Barnaby (1978). "The Apollo-Saturn IB Space Vehicle". Moonport: A History of Apollo Launch Facilities and Operations. NASA. Archived from the original on 24 March 2016. Retrieved 3 February 2016.
^ ^a ^b ^c ^d "Saturn IB History". Archived from the original on January 4, 2013. Retrieved 2009-11-01.{{cite web}}: CS1 maint: unfit URL (link)
^ "Saturn I".
^ NASA Marshall Spaceflight Center, Skylab Saturn IB Flight Manual (MSFC-MAN-206), 30 September 1972
^ ^a ^b ^c Skylab Saturn 1B Flight Manual - (PDF), NASA, September 30, 1972, retrieved July 8, 2020
^ ^a ^b ^c Reynolds, David West (2006). Kennedy Space Center: Gateway to Space. Richmond Hill, Ontario: Firefly Books Ltd. pp. 154–157. ISBN 978-1-55407-039-8.
^ ^a ^b "Historic Alabama welcome center rocket dismantling begins". 14 September 2023. Retrieved 2023-09-20.
^ Dooling, Dave (May 6, 1979). "Space and Rocket Plans Summer Celebration". The Huntsville Times.
^ Hughes, Bayne (April 6, 2014). "Iconic rocket due for repair". The Decatur Daily. Retrieved April 8, 2014.
^ "SP-4221 The Space Shuttle Decision- Chapter 6: Economics and the Shuttle". NASA. Retrieved 2011-01-15.

External links

http://www.apollosaturn.com/
http://www.spaceline.org/rocketsum/saturn-Ib.html
NASA Marshall Spaceflight Center, "Skylab Saturn IB Flight Manual" (PDF). (19.8 MB), 30 September 1972
"Saturn launch vehicles" (PDF). Archived from the original (PDF) on 2005-04-16. (61.2 MB)

[4] Pronounced "saturn one bee"

[AS201-1] Postlaunch report for mission AS-201 (Apollo spacecraft 009) - (PDF), NASA, May 1966, retrieved March 18, 2011

[astronautix-2] Wade, Mark. "Saturn IB". Encyclopedia Astronautica. Archived from the original on May 14, 2011. Retrieved March 17, 2011.

[3] Hornung, John (2013). Entering the Race to the Moon: Autobiography of an Apollo Rocket Scientist. Williamsburg, Virginia: Jack Be Nimble Publishing. ISBN 9780983044178.

[5] Benson, Charles D.; Faherty, William Barnaby (1978). "The Apollo-Saturn IB Space Vehicle". Moonport: A History of Apollo Launch Facilities and Operations. NASA. Archived from the original on 24 March 2016. Retrieved 3 February 2016.

[SIB_final_use-6] "Saturn IB History". Archived from the original on January 4, 2013. Retrieved 2009-11-01.{{cite web}}: CS1 maint: unfit URL (link)

[7] "Saturn I".

[8] NASA Marshall Spaceflight Center, Skylab Saturn IB Flight Manual (MSFC-MAN-206), 30 September 1972

[SL_SAT1B_FM-9] Skylab Saturn 1B Flight Manual - (PDF), NASA, September 30, 1972, retrieved July 8, 2020

[West_2006-10] Reynolds, David West (2006). Kennedy Space Center: Gateway to Space. Richmond Hill, Ontario: Firefly Books Ltd. pp. 154–157. ISBN 978-1-55407-039-8.

[Historic_Alabama_welcome_center_rocket_dismantling_begins-11] "Historic Alabama welcome center rocket dismantling begins". 14 September 2023. Retrieved 2023-09-20.

[12] Dooling, Dave (May 6, 1979). "Space and Rocket Plans Summer Celebration". The Huntsville Times.

[13] Hughes, Bayne (April 6, 2014). "Iconic rocket due for repair". The Decatur Daily. Retrieved April 8, 2014.

[SP4221Ch6-14] "SP-4221 The Space Shuttle Decision- Chapter 6: Economics and the Shuttle". NASA. Retrieved 2011-01-15.

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v t e Apollo program hardware
Launch vehicles	Little Joe II Saturn I Saturn IB Saturn V
Launch vehicle components	F-1 engine J-2 engine Instrument unit Launch Vehicle Digital Computer
Spacecraft	Apollo Apollo command module Columbia Apollo service module Apollo Lunar Module Eagle
Spacecraft components	Apollo Abort Guidance System Apollo Docking Mechanism Apollo Guidance Computer Lunar Sounder Experiment Primary guidance, navigation, and control system Apollo Telescope Mount Apollo TV camera Descent propulsion system Ascent propulsion system Scimitar antenna
Space suits	Apollo/Skylab A7L Beta cloth Thermal Micrometeoroid Garment
Lunar surface equipment	Portable Life Support System Lunar Roving Vehicle Lunar Laser Ranging experiment list of retroreflectors Solar Wind Composition Experiment Apollo Lunar Surface Experiments Package Active Seismic Experiment Apollo 12 Passive Seismic Experiment Apollo 14 Passive Seismic Experiment Charged Particle Lunar Environment Experiment Lunar Ejecta and Meteorites Experiment Solar Wind Spectrometer Experiment Modular Equipment Transporter Lunar Seismic Profiling Experiment Lunar Surface Gravimeter Lunar Surface Magnetometer Lunar Traverse Gravimeter Cold Cathode Gauge Experiment Heat Flow Experiment Suprathermal Ion Detector Experiment
Ground support	Mobile Launcher Launch Umbilical Tower Crawler-transporter Lunar Landing Research Vehicle Mobile quarantine facility
Ceremonial	Lunar plaque Lunar Flag Assembly Fallen Astronaut Apollo 11 goodwill messages
Related	Lunar escape systems Rendezvous Docking Simulator Moon Museum
Category:Apollo program hardware

v t e Orbital launch systems
List of orbital launch systems Comparison of orbital launch systems
Current	Angara 1.2 A5 Ariane 6 Atlas V Ceres 1 1S Chollima-1 Electron Falcon 9 Block 5 Falcon Heavy Firefly Alpha Gravity-1 GSLV H-IIA H3 Hyperbola-1 Jielong 1 3 KAIROS^† Kaituozhe 2 Kinetica 1 Kuaizhou 1 1A 11 Long March 2C 2D 2F 3A 3B/E 3C 4B 4C 5 5B 6 6A 7 7A 8 11 11H 12 LVM3 Minotaur I IV V C Nuri OS-M1^† Pegasus XL Proton-M PSLV Qaem 100 Qased Shavit 2 Simorgh SLS Block 1 Soyuz-2 2.1a / STA 2.1b / STB 2-1v SSLV Starship Tianlong-2 Unha Vega C Vulcan Centaur Zhuque 2
In development	Antares 330 Bloostar Cyclone-4M Deca Epsilon S Eris Gravity-2 Hyperbola-2 Irtysh Kuaizhou 21 31 Long March 9 10 Miura 5 MLV Neutron New Glenn New Line 1 NGLV Nova OS-M 2 4 Orbex Prime Pallas-1 Red Dwarf SLS Block 1B Block 2 Soyuz-7 Terran R Tianlong-3 VLM Vega E Zero Zhuque 3 Zuljanah
Retired	Antares 110 120 130^† 230 230+ Ariane 1 2 3 4 5 ASLV Athena I II Atlas B D E/F G H I II III LV-3B SLV-3 Able^† Agena Centaur Black Arrow Conestoga^† Delta A B C D E G J L M N 0100 1000 2000 3000 4000 5000 II III IV IV Heavy Diamant Dnepr Energia Epsilon Europa I^† II^† Falcon 1 Falcon 9 v1.0 v1.1 v1.2 "Full Thrust" Feng Bao 1 GSLV Mk I H-I H-II H-IIB Juno I Juno II Kaituozhe-1 Kosmos original 1 2/2I 3 3M Lambda 4S LauncherOne Long March 1 1D^† 2A 2E 3 3B 4A Mu 4S 3C 3H 3S 3SII V N1^† N-I N-II Naro-1 Paektusan^† Pilot-2^† R-7 Luna Molniya M L Polyot Soyuz original FG L M U U2 Soyuz/Vostok Sputnik Voskhod Vostok L K 2 2M R-29 Shtil' Volna^† Rocket 3 RS1^† Safir 1 1A 1B Saturn I IB V Scout X-1 Blue Scout II^† X-2^† X-2M X-3 X-3M X-4 X-2B^† B A B-1 D-1 A-1 E-1 F-1 G-1 Shavit original 1 SLV Space Shuttle SPARK^† Sparta SS-520 Start-1 Terran 1^† Thor Able Ablestar 1 2 Agena A B D Burner 1 2 Delta DSV-2U Thorad-Agena SLV-2G SLV-2H Titan II GLV IIIA IIIB IIIC IIID IIIE 34D 23G CT-3 IV Tsyklon R-36-O original 2 3 Universal Rocket UR-500 Proton Proton-K Rokot Strela Vanguard Vega original VLS-1^† Zenit 2 2M 2FG 3SL 3SLB 3F Zhuque 1^†
Classes	Sounding rocket Small-lift launch vehicle Medium-lift launch vehicle Heavy-lift launch vehicle Super heavy-lift launch vehicle
This Template lists historical, current, and future space rockets that at least once attempted (but not necessarily succeeded in) an orbital launch or that are planned to attempt such a launch in the future Symbol ^† indicates past or current rockets that attempted orbital launches but never succeeded (never did or has yet to perform a successful orbital launch)

v t e Orbital launch systems developed in the United States
Active	Atlas V**^†† Electron Falcon 9 Block 5 Falcon Heavy Firefly Alpha Minotaur I IV V C Pegasus XL SLS Block 1 Vulcan Centaur
In development	Antares 330 Daytona I MLV New Glenn Neutron Nova Red Dwarf SLS Block 1B Block 2 Starship Terran R
Retired	Antares 110/120/130/230/230+^††† Athena I II Atlas B D E/F G H I II III LV-3B SLV-3 Able Agena Centaur Conestoga Delta A B C D E G J L M N 0100 1000 2000 3000 4000 5000 II III IV IV Heavy Falcon 1 Falcon 9 v1.0 v1.1 v1.2 "Full Thrust" H-I* Juno I Juno II LauncherOne N-I* N-II* Pilot Rocket 3 RS1^† Saturn I IB V Scout Space Shuttle SPARK Sparta Terran 1 Thor Able Ablestar Agena Burner Delta DSV-2U Thorad-Agena Titan II GLV IIIA IIIB IIIC IIID IIIE 34D 23G CT-3 IV Vanguard
* - Japanese projects using US rockets or stages ** - uses Russian engines ^† - never succeeded ^†† - no new orders accepted ^††† - used Ukrainian first stage

v t e Saturn launch vehicle family
Early proposals	Juno V Saturn A-1 A-2 B-1
"C" series	Saturn C-1 C-2 C-3 C-4 C-5 C-5N C-8
Saturn I series	Saturn I IB IB-CE IB-A IB-B IB-C IB-D INT-05 INT-11 INT-12 INT-13 INT-14 INT-15 INT-16 INT-27 LCB
Saturn II series	Saturn II INT-17 INT-18 INT-19
Saturn V series	Saturn V MLV V ELV INT-20 INT-21 INT-23 INT-24 INT-25 Saturn-Shuttle Saturn V-3 V-A V-B V-C V-D V-Centaur Jarvis