Saturn II

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  1. 1 2 3 4 Includes S-II/S-IVB interstage
  2. 1 2 Includes Instrument Unit

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<span class="mw-page-title-main">S-IVB</span> Third stage on the Saturn V and second stage on the Saturn IB

The S-IVB was the third stage on the Saturn V and second stage on the Saturn IB launch vehicles. Built by the Douglas Aircraft Company, it had one J-2 rocket engine. For lunar missions it was fired twice: first for Earth orbit insertion after second stage cutoff, and then for translunar injection (TLI).

<span class="mw-page-title-main">AS-203</span> Uncrewed flight of the Saturn IB rocket, July 5, 1966

AS-203 was an uncrewed flight of the Saturn IB rocket on July 5, 1966. It carried no command and service module, as its purpose was to verify the design of the S-IVB rocket stage restart capability that would later be used in the Apollo program to boost astronauts from Earth orbit to a trajectory towards the Moon. It achieved its objectives, but the stage was inadvertently destroyed after four orbits.

<span class="mw-page-title-main">Delta (rocket family)</span> Rocket family

The Delta rocket family is a versatile range of American rocket-powered expendable launch systems that has provided space launch capability in the United States since 1960. Japan also launched license-built derivatives from 1975 to 1992. More than 300 Delta rockets have been launched with a 95% success rate. The series has been phased-out in favor of the Vulcan Centaur, with only the Delta IV Heavy rocket remaining in use as of June 2023.

<span class="mw-page-title-main">Black Brant (rocket)</span> Family of Canadian-designed sounding rockets

The Black Brant is a family of Canadian-designed sounding rockets originally built by Bristol Aerospace, since absorbed by Magellan Aerospace in Winnipeg, Manitoba. Over 800 Black Brants of various versions have been launched since they were first produced in 1961, and the type remains one of the most popular sounding rockets. They have been repeatedly used by the Canadian Space Agency and NASA.

<span class="mw-page-title-main">Saturn IB</span> American rocket used in the Apollo program during the 1960s and 70s

The Saturn IB(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, with the S-IVB. 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.

<span class="mw-page-title-main">Solid rocket booster</span> Solid propellant motor used to augment the thrust of a rocket

A solid rocket booster (SRB) is a large solid propellant motor used to provide thrust in spacecraft launches from initial launch through the first ascent. Many launch vehicles, including the Atlas V, SLS and Space Shuttle, have used SRBs to give launch vehicles much of the thrust required to place the vehicle into orbit. The Space Shuttle used two Space Shuttle SRBs, which were the largest solid propellant motors ever built and the first designed for recovery and reuse. The propellant for each solid rocket motor on the Space Shuttle weighed approximately 500,000 kilograms.

<span class="mw-page-title-main">S-IC</span> First stage of the Saturn V rocket

The S-IC was the first stage of the American Saturn V rocket. The S-IC stage was manufactured by the Boeing Company. Like the first stages of most rockets, most of its mass of more than 2,000 t (4,400,000 lb) at launch was propellant, in this case RP-1 rocket fuel and liquid oxygen (LOX) oxidizer. It was 42 m (138 ft) tall and 10 m (33 ft) in diameter. The stage provided 34,500 kN (7,750,000 lbf) of thrust at sea level to get the rocket through the first 61 km (38 mi) of ascent. The stage had five F-1 engines in a quincunx arrangement. The center engine was fixed in position, while the four outer engines could be hydraulically gimballed to control the rocket.

<span class="mw-page-title-main">Delta IV</span> Active expendable launch system in the Delta rocket family

Delta IV was a group of five expendable launch systems in the Delta rocket family introduced in the early 2000s. Originally designed by Boeing's Defense, Space and Security division for the Evolved Expendable Launch Vehicle (EELV) program, the Delta IV became a United Launch Alliance (ULA) product in 2006. The Delta IV was primarily a launch vehicle for United States Air Force (USAF) military payloads, but was also used to launch a number of United States government non-military payloads and a single commercial satellite.

The Saturn I was a rocket designed as the United States' first medium lift launch vehicle for up to 20,000-pound (9,100 kg) low Earth orbit payloads. The rocket's first stage was built as a cluster of propellant tanks engineered from older rocket tank designs, leading critics to jokingly refer to it as "Cluster's Last Stand". Its development was taken over from the Advanced Research Projects Agency in 1958 by the newly formed civilian NASA. Its design proved sound and flexible. It was successful in initiating the development of liquid hydrogen-fueled rocket propulsion, launching the Pegasus satellites, and flight verification of the Apollo command and service module launch phase aerodynamics. Ten Saturn I rockets were flown before it was replaced by the heavy lift derivative Saturn IB, which used a larger, higher total impulse second stage and an improved guidance and control system. It also led the way to development of the super-heavy lift Saturn V which carried the first men to landings on the Moon in the Apollo program.

<span class="mw-page-title-main">Little Joe II</span> American rocket

Little Joe II was an American rocket used from 1963 to 1966 for five uncrewed tests of the Apollo spacecraft launch escape system (LES), and to verify the performance of the command module parachute recovery system in abort mode. It was named after a similar rocket designed for the same function in Project Mercury. Launched from White Sands Missile Range in New Mexico, it was the smallest of four launch rockets used in the Apollo program.

<span class="mw-page-title-main">Titan IV</span> Expendable launch system used by the US Air Force

Titan IV was a family of heavy-lift space launch vehicles developed by Martin Marietta and operated by the United States Air Force from 1989 to 2005. Launches were conducted from Cape Canaveral Air Force Station, Florida and Vandenberg Air Force Base, California.

<span class="mw-page-title-main">Titan IIIB</span>

Titan IIIB was the collective name for a number of derivatives of the Titan II ICBM and Titan III launch vehicle, modified by the addition of an Agena upper stage. It consisted of four separate rockets. The Titan 23B was a basic Titan II with an Agena upper stage, and the Titan 24B was the same concept, but using the slightly enlarged Titan IIIM rocket as the base. The Titan 33B was a Titan 23B with the Agena enclosed in an enlarged fairing, in order to allow larger payloads to be launched. The final member of the Titan IIIB family was the Titan 34B which was a Titan 24B with the larger fairing used on the Titan 33B.

The Saturn Vehicle Evaluation Committee, better known as the Silverstein Committee, was a US government commission assembled in 1959 to recommend specific directions that NASA could take with the Saturn rocket program. The committee was chaired by Abe Silverstein, a long-time NASA engineer, with the express intent of selecting upper stages for the Saturn after a disagreement broke out between the Air Force and Army over its development. During the meetings the Committee members outlined a number of different potential designs, including the low-risk solution von Braun was developing with existing ICBM airframes, as well as versions using entirely new upper stages developed to take full advantage of the booster stage. The advantages of using new uppers were so great that the committee won over an initially skeptical von Braun, and the future of the Saturn program changed forever.

A liquid rocket booster (LRB) uses liquid fuel and oxidizer to give a liquid-propellant or hybrid rocket an extra boost at take-off, and/or increase the total payload that can be carried. It is attached to the side of a rocket. Unlike solid rocket boosters, LRBs can be throttled down if the engines are designed to allow it, and can be shut down safely in an emergency for additional escape options in human spaceflight.

<span class="mw-page-title-main">Modular rocket</span> Rocket with interchangeable components

A modular rocket is a kind of multistage rocket which has components that can interchanged for different missions. Several such rockets use similar concepts such as unified modules to minimize expenses on manufacturing, transportation and for optimization of support infrastructure for flight preparations.

<span class="mw-page-title-main">Saturn INT-20</span>

The Saturn INT-20 was a proposed intermediate-payload follow-on from the Apollo Saturn V launch vehicle. A conical-form interstage would be fitted on top of the S-IC stage to support the S-IVB stage, so it could be considered either a retrofitted Saturn IB with a more powerful first stage, or a stubby, cut-down Saturn V without the S-II second stage.

The Saturn MLV was a proposed concept family of rockets, intended as a follow-on to the Saturn V. MLV stands for "Modified Launch Vehicle".

<span class="mw-page-title-main">Saturn C-4</span> Proposed NASA super-heavy-lift rocket

The Saturn C-4 was the fourth rocket in the Saturn C series studied from 1959 to 1962. The C-4 design was proposed in 1960 for a three-stage launch vehicle that could launch 99,000 kg (218,000 lb) to low Earth orbit and send 32,000 kg (70,000 lb) to the Moon via trans-lunar injection. It met the initial requirements for a lunar orbit rendezvous and lunar landing mission.

<span class="mw-page-title-main">Saturn C-3</span> Third rocket in the Saturn C series studied from 1959 to 1962

The Saturn C-3 was the third rocket in the Saturn C series studied from 1959 to 1962. The design was for a three-stage launch vehicle that could launch 45,000 kilograms (99,000 lb) to low Earth orbit and send 18,000 kilograms (40,000 lb) to the Moon via trans-lunar injection.

<span class="mw-page-title-main">Saturn V</span> American super heavy-lift expendable rocket

The Saturn V is a retired American super heavy-lift launch vehicle developed by NASA under the Apollo program for human exploration of the Moon. The rocket was human-rated, had three stages, and was powered with liquid fuel. Flown from 1967 to 1973, it was used for nine crewed flights to the Moon, and to launch Skylab, the first American space station.

References

  1. 1 2 Final Report - Studies of Improved Saturn V Vehicles and Intermediate Payload Vehicles (P-115) (PDF). Boeing Space Division. October 1966. Archived from the original (PDF) on 2006-06-14.
  2. "J-2". www.astronautix.com. Retrieved 2024-01-18.
  3. 1 2 "Saturn INT-17". www.astronautix.com. Retrieved 2024-01-18.
  4. "Saturn INT-18". www.astronautix.com. Retrieved 2024-01-18.
  5. "Saturn INT-19". www.astronautix.com. Retrieved 2024-01-18.
Saturn II
Saturn II.svg
Saturn II proposals: INT-17, INT-18, INT-19.
FunctionOrbital launch vehicle
Manufacturer North American (S-II)
Douglas (S-IVB)
Country of originUnited States
Size
Height167 feet (51 m)
Diameter33 feet (10 m)
Mass1,112,000 to 4,178,200 pounds (504,400 to 1,895,200 kg)
Stages2
Capacity
Payload to LEO (100 nmi (185 km), 28° inclination)
Mass47,000 to 146,400 pounds (21,300 to 66,400 kg)
Associated rockets
Family Saturn
Derivative work
  • INT-17
  • INT-18
  • INT-19
Launch history
StatusStudy 1966
Launch sites Kennedy Space Center Launch Complex 39,
Total launches0
Boosters (INT-18) – UA1207
No. boosters2 or 4
Powered by1
Maximum thrust1,600,000 lbf (7,100 kN) SL
Total thrust3,200,000 lbf (14,000 kN) or 6,400,000 lbf (28,000 kN) SL
Specific impulse 272 seconds SL
Burn time120 seconds
Propellant APCP