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The Saturn V reached 400 feet per second (120 m/s) at over 1 mile (1,600 m) in altitude. Much of the early portion of the flight was spent gaining altitude, with the required velocity coming later. The Saturn V broke the sound barrier at just over 1 minute at an altitude of between 3.45 and 4.6 miles (5.55 and 7.40 km). At this point, shock ...
S-IC-T was planned as a test rocket only and not to be used in the later Apollo program. The Saturn V rocket was used in the Apollo program to depart Earth's gravity. S-IC-T, like all following Saturn V's S-IC rockets used five Rocketdyne F-1 engines. The Rocketdyne F-1 engine was first tested in March 1959 and delivered to NASA in October 1963.
Saturn IB – nine launches; a refined version of the Saturn I with a more powerful first stage (designated the S-IB) and using the Saturn V's S-IVB as a second stage. These carried the first Apollo flight crew, plus three Skylab and one Apollo-Soyuz crews, into Earth orbit.
Diagram of Saturn V Launch Vehicle. The Saturn V consisted of three stages and an Instrument Unit (IU). The first stage, S-IC, delivered 7,610,000 pounds-force (33.9 MN) thrust and delivered the other stages to 200,000 feet (61 km). [12] Afterwards, it was jettisoned to fall into the Atlantic Ocean and the second stage continued acceleration. [12]
The S-IVB (pronounced "S-four-B") 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).
The S-V would ultimately fly as the third stage on early launches of the Saturn I. Convair delivered two S-V stages in February 1961 [1] with one being flown on SA-1 attached to an also inert S-IV, the second was used for dynamic testing of the complete Saturn I before being later flown. In May 1961 NASA eliminated the requirement for all ...
The J-2, commonly known as Rocketdyne J-2, was a liquid-fuel cryogenic rocket engine used on NASA's Saturn IB and Saturn V launch vehicles. Built in the United States by Rocketdyne, the J-2 burned cryogenic liquid hydrogen (LH 2) and liquid oxygen (LOX) propellants, with each engine producing 1,033.1 kN (232,250 lb f) of thrust in vacuum.
It was the first flight of the first and second stages of the Saturn V (the S-IVB stage had flown on the Saturn IB launch vehicles), the first launch of the complete Saturn V, the first restart of the S-IVB in orbital flight, the first liftoff from Complex 39, the first flight test of the Block II command module heatshield, the first flight of ...