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S-IB
The S-IB stage was the first stage of the Saturn IB launch vehicle, which was used for Earth orbital missions. It was composed of nine propellant containers, eight fins, a thrust structure assembly, eight H-1 rocket engines, and many other components. It also contained the ODOP transponder. The propellant containers consisted of eight Redstone-derived tanks (four holding liquid oxygen (LOX) and four holding RP-1) clustered around a Jupiter rocket-derived tank containing LOX. The four outboard engines gimballed to steer the rocket in flight, which required a few more engine components. The S-IB burned for nearly 2.5 minutes before separating at an altitude of . Specifications *Height: *Diameter: *Number of fins: 8 *Finspan: *Engines: 8 Rocketdyne H-1 *Thrust: *Fuel: RP-1 (Refined kerosene) 41,000 US gal (155 m3) *Oxidizer: Liquid oxygen Oxygen is the chemical element with the symbol O and atomic number 8. It is a member of the chalcogen group in the peri ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Saturn IB
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 (, 43,380,000 lb-sec total impulse), with the S-IVB (, 96,000,000 lb-sec total impulse). The S-IB first stage also increased the S-I baseline's thrust from to and propellant load by 3.1%. This increased the Saturn I's low Earth orbit payload capability from to , 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 inj ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
H-1 (rocket Engine)
The Rocketdyne H-1 was a thrust liquid-propellant rocket engine burning LOX and RP-1. The H-1 was developed for use in the S-I and S-IB first stages of the Saturn I and Saturn IB rockets, respectively, where it was used in clusters of eight engines. After the Apollo program, surplus H-1 engines were rebranded and reworked as the Rocketdyne RS-27 engine with first usage on the Delta 2000 series in 1974. The RS-27 variant is also used on the Delta II and Delta III. History Early engines The H-1 is one of a series of engines developed from the wartime V-2 ballistic missile. During the war, North American Aviation (NAA) was given several V-2 engines to examine and convert from metric to SAE measurements. They formed their "Propulsion Division" to handle this work, later becoming Rocketdyne. NAA had also been given a wealth of technical documentation on the engine. Engineers studying them came across plans to improve the V-2 engine using a new "waterfall" fuel injector. The ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Rocketdyne H-1
The Rocketdyne H-1 was a thrust liquid-propellant rocket engine burning LOX and RP-1. The H-1 was developed for use in the S-I and S-IB first stages of the Saturn I and Saturn IB rockets, respectively, where it was used in clusters of eight engines. After the Apollo program, surplus H-1 engines were rebranded and reworked as the Rocketdyne RS-27 engine with first usage on the Delta 2000 series in 1974. The RS-27 variant is also used on the Delta II and Delta III. History Early engines The H-1 is one of a series of engines developed from the wartime V-2 ballistic missile. During the war, North American Aviation (NAA) was given several V-2 engines to examine and convert from metric to SAE measurements. They formed their "Propulsion Division" to handle this work, later becoming Rocketdyne. NAA had also been given a wealth of technical documentation on the engine. Engineers studying them came across plans to improve the V-2 engine using a new "waterfall" fuel injector. The ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Saturn I
The Saturn I was a rocket designed as the United States' first medium lift launch vehicle for up to low Earth orbit payloads.Terminology has changed since the 1960s; back then, 20,000 pounds was considered "heavy lift". 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 ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
ODOP
The ODOP (Offset DOPpler) radar tracking system is essentially the same as the UDOP system used for many years at the Atlantic Missile Range, but ODOP operates at different frequencies. It is a phase-coherent, multistation Doppler tracking system which measures position of a vehicle equipped with the ODOP transponder. ODOP stations are located at and around Cape Kennedy. The ODOP transponder is carried in the first stage ( S-IB or S-IC) of the Saturn vehicles and, therefore, ODOP tracking data is limited to the flight of the first stage only. The ODOP tracking system provides data immediately following lift-off while other tracking systems cannot "see" the vehicle or their accuracy is reduced by multipath propagation during the early phase of the flight. The ODOP system is a radar interferometer tracking system which determines the position of a vehicle-borne transponder. The ground transmitter radiates a CW signal of 890 MHz to the transponder in the vehicle. The trans ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Chrysler
Stellantis North America (officially FCA US and formerly Chrysler ()) is one of the " Big Three" automobile manufacturers in the United States, headquartered in Auburn Hills, Michigan. It is the American subsidiary of the multinational automotive company Stellantis. In addition to the Chrysler brand, Stellantis North America sells vehicles worldwide under the Dodge, Jeep, and Ram nameplates. It also includes Mopar, its automotive parts and accessories division, and SRT, its performance automobile division. The original Chrysler Corporation was founded in 1925 by Walter Chrysler from the remains of the Maxwell Motor Company. It was acquired by Daimler-Benz, which in 1998 renamed itself DaimlerChrysler. After Daimler divested Chrysler in 2007, the company operated as Chrysler LLC (2007–2009) and Chrysler Group LLC (2009–2014) before being acquired by Fiat S.p.A. and becoming a subsidiary of the newly formed Fiat Chrysler Automobiles ("FCA") in 2014. Chrysler in 2021 is a ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
RP-1
RP-1 (alternatively, Rocket Propellant-1 or Refined Petroleum-1) is a highly refined form of kerosene outwardly similar to jet fuel, used as rocket fuel. RP-1 provides a lower specific impulse than liquid hydrogen (LH2), but is cheaper, is stable at room temperature, and presents a lower explosion hazard. RP-1 is far denser than LH2, giving it a higher energy density (though its specific energy is lower). RP-1 also has a fraction of the toxicity and carcinogenic hazards of hydrazine, another room-temperature liquid fuel. Usage and history RP-1 is a fuel in the first-stage boosters of the Electron, Soyuz, Zenit, Delta I-III, Atlas, Falcon, Antares, and Tronador II rockets. It also powered the first stages of the Energia, Titan I, Saturn I and IB, and Saturn V. The Indian Space Research Organization (ISRO) is also developing an RP-1 fueled engine for its future rockets. Development During and immediately after World War II, alcohols (primarily ethanol, occasionally me ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Multistage Rocket
A multistage rocket or step rocket is a launch vehicle that uses two or more rocket ''stages'', each of which contains its own engines and propellant. A ''tandem'' or ''serial'' stage is mounted on top of another stage; a ''parallel'' stage is attached alongside another stage. The result is effectively two or more rockets stacked on top of or attached next to each other. Two-stage rockets are quite common, but rockets with as many as five separate stages have been successfully launched. By jettisoning stages when they run out of propellant, the mass of the remaining rocket is decreased. Each successive stage can also be optimized for its specific operating conditions, such as decreased atmospheric pressure at higher altitudes. This ''staging'' allows the thrust of the remaining stages to more easily accelerate the rocket to its final speed and height. In serial or tandem staging schemes, the first stage is at the bottom and is usually the largest, the second stage and subseq ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Rocket Engine
A rocket engine uses stored rocket propellants as the reaction mass for forming a high-speed propulsive jet of fluid, usually high-temperature gas. Rocket engines are reaction engines, producing thrust by ejecting mass rearward, in accordance with Newton's third law. Most rocket engines use the combustion of reactive chemicals to supply the necessary energy, but non-combusting forms such as cold gas thrusters and nuclear thermal rockets also exist. Vehicles propelled by rocket engines are commonly called rockets. Rocket vehicles carry their own oxidiser, unlike most combustion engines, so rocket engines can be used in a vacuum to propel spacecraft and ballistic missiles. Compared to other types of jet engine, rocket engines are the lightest and have the highest thrust, but are the least propellant-efficient (they have the lowest specific impulse). The ideal exhaust is hydrogen, the lightest of all elements, but chemical rockets produce a mix of heavier species, reducin ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
PGM-11 Redstone
The PGM-11 Redstone was the first large American ballistic missile. A short-range ballistic missile (SRBM), it was in active service with the United States Army in West Germany from June 1958 to June 1964 as part of NATO's Cold War defense of Western Europe. It was the first US missile to carry a live nuclear warhead, in the 1958 Pacific Ocean weapons test, Hardtack Teak. The Redstone was a direct descendant of the German V-2 rocket, developed primarily by a team of German rocket engineers brought to the United States after World War II. The design used an upgraded engine from Rocketdyne that allowed the missile to carry the W39 warhead which weighed with its reentry vehicle to a range of about . Redstone's prime contractor was the Chrysler Corporation. The Redstone spawned the Redstone rocket family which holds a number of firsts in the US space program, notably launching the first US astronaut. It was retired by the Army in 1964 and replaced by the solid-fueled MGM-31 Pe ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Liquid Oxygen
Liquid oxygen—abbreviated LOx, LOX or Lox in the aerospace, submarine and gas industries—is the liquid form of molecular oxygen. It was used as the oxidizer in the first liquid-fueled rocket invented in 1926 by Robert H. Goddard, an application which has continued to the present. Physical properties Liquid oxygen has a pale blue color and is strongly paramagnetic: it can be suspended between the poles of a powerful horseshoe magnet. Liquid oxygen has a density of , slightly denser than liquid water, and is cryogenic with a freezing point of and a boiling point of at . Liquid oxygen has an expansion ratio of 1:861 under and , and because of this, it is used in some commercial and military aircraft as a transportable source of breathing oxygen. Because of its cryogenic nature, liquid oxygen can cause the materials it touches to become extremely brittle. Liquid oxygen is also a very powerful oxidizing agent: organic materials will burn rapidly and energetically in l ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
PGM-19 Jupiter
The PGM-19 Jupiter was the first nuclear armed, medium-range ballistic missile (MRBM) of the United States Air Force (USAF). It was a liquid-propellant rocket using RP-1 fuel and LOX oxidizer, with a single Rocketdyne LR79-NA (model S-3D) rocket engine producing of thrust. It was armed with the W49 nuclear warhead. The prime contractor was the Chrysler Corporation. The Jupiter was originally designed by the US Army, which was looking for a highly accurate missile designed to strike enemy states such as Communist China and USSR. The US Navy also expressed an interest in the design as an SLBM but left the collaboration to work on their Polaris. Jupiter retained the short, squat shape intended to fit in naval submarines. Development history Initial concept Jupiter traces its history ultimately to the PGM-11 Redstone missile, the US's first nuclear ballistic missile. While it was entering service, Wernher von Braun's Army Ballistic Missile Agency (ABMA) team at Redstone A ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
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