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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 ...
The American Saturn MLV family of rockets was proposed in 1965 by NASA as successors to the Saturn V rocket. [71] It would have been able to carry up to 160,880 kg (354,680 lb) to low Earth orbit. The Nova designs were also studied by NASA before the agency chose the Saturn V in the early 1960s [ 72 ] Nova was cancelled in 1964 and had reusable ...
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:
C-1 – Saturn lower stage, proposed S-IV second stage (similar to the actual Saturn I). C-2 – Saturn lower stage, proposed S-II second stage, proposed S-IV third stage. C-3 , C-4 , and C-5 – all based on different variations of a new lower stage using F-1 engines, variations of proposed S-II second stages, and proposed S-IV third stages ...
The S-II (pronounced "S-two") was the second stage of the Saturn V rocket. It was built by North American Aviation. Using liquid hydrogen (LH2) and liquid oxygen (LOX) it had five J-2 engines in a quincunx pattern. The second stage accelerated the Saturn V through the upper atmosphere with 1,000,000 pounds-force (4.4 MN) of thrust.
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 ...
Super-heavy lift vehicle: > 50,000 kilograms (110,000 lb) - e.g. Saturn V [10] Sounding rockets are similar to small-lift launch vehicles, however they are usually even smaller and do not place payloads into orbit. A modified SS-520 sounding rocket was used to place a 4-kilogram payload into orbit in 2018. [11]
weight ratio (kg) (lb) (kN) (lbf) RD-0410 nuclear rocket engine [1] [2] 2,000 4,400 35.2 7,900 1.8 J58 jet engine (SR-71 Blackbird) [3] [4] 2,722 6,001 150 34,000 5.2 Rolls-Royce/Snecma Olympus 593 turbojet with reheat [5] 3,175 7,000 169.2 38,000 5.4 Pratt & Whitney F119 [6] 1,800 3,900 91 20,500 7.95 RD-0750 rocket engine, three-propellant ...
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