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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 ...
Both the Saturn IB and the Saturn V would use a S-IVB, though the IB would use it as its second, final stage, rather than the third stage as on the Saturn V. Thus, many of the flight qualifications for the payload the Saturn V would carry could be resolved without having to expend one of the large launch vehicles. [10]
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.
First long-time space soak and firing of a nuclear propulsion module. (Note: In this context, "space soak" means “to leave in space for an extended period of time” [3]) First long-time simulated crewed planetary mission operation. First full planetary simulated mission in Earth orbit. First crewed planet reentry simulation.
A boilerplate spacecraft, also known as a mass simulator, is a nonfunctional craft or payload that is used to test various configurations and basic size, load, and handling characteristics of rocket launch vehicles.
The Propulsion and Structural Test Facility, also known as Building 4572 and the Static Test Stand, is a rocket testing facility of the George C. Marshall Space Flight Center in Huntsville, Alabama. Built in 1957, it was the site where the first single-stage rockets with multiple engines were tested. [ 4 ]
During their two and a half minutes of operation, the five F-1s propelled the Saturn V vehicle to a height of 42 miles (222,000 ft; 68 km) and a speed of 6,164 mph (9,920 km/h). The combined flow rate of the five F-1s in the Saturn V was 3,357 US gal (12,710 L) [5] or 28,415 lb (12,890 kg) per second.
The Crawlerway was originally designed to support the weight of the Saturn V rocket and its payload, plus the Launch Umbilical Tower and mobile launcher platform, atop a crawler-transporter during the Apollo program. It was also used from 1981 to 2011 to transport the lighter Space Shuttles to their launch pads.