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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 ...
Launch Complex 39A (LC-39A) is the first of Launch Complex 39's three launch pads, located at NASA's Kennedy Space Center in Merritt Island, Florida.The pad, along with Launch Complex 39B, was first constructed in the 1960s to accommodate the Saturn V launch vehicle, and has been used to support NASA crewed space flight missions, including the historic Apollo 11 moon landing and the Space Shuttle.
The Saturn C-5 (later given the name Saturn V), the most powerful of the Silverstein Committee's configurations, was selected as the most suitable design. At the time the mission mode had not been selected, so they chose the most powerful booster design in order to ensure that there would be ample power. [ 24 ]
A 1968 proposal for a Saturn V ELV (MLV-SAT-V-25(S)U) According to the 1968 NASA document "Integrated Manned Interplanetary Spacecraft Concept Definition", there was a planned schedule for exploration under the ELV program. [2] After the first crewed Apollo lunar landing, NASA was hoping to progress through the following list:
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.
The propellant tanks on Super Heavy are separated by a common bulkhead, similar to the ones used on the S-II and S-IVB stages on the Saturn V rocket. [ 10 ] [ 11 ] After Starship's second flight test , the common dome's design was changed to a more elliptical dome, [ 12 ] which changed the propellant capacity of both tanks by an unknown, but ...
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.
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]