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Apollo 8 launched on December 21, 1968, and was the second crewed spaceflight mission flown in the United States Apollo space program (the first, Apollo 7, stayed in Earth orbit). Apollo 8 was the third flight and the first crewed launch of the Saturn V rocket.
A free-return trajectory may be the initial trajectory to allow a safe return in the event of a systems failure; this was applied in the Apollo 8, Apollo 10, and Apollo 11 lunar missions. In such a case a free return to a suitable reentry situation is more useful than returning to near the Earth, but then needing propulsion anyway to prevent ...
Orbital mechanics are used to calculate flight in orbit about a central body. For sufficiently high orbits (generally at least 190 kilometers (100 nautical miles) in the case of Earth), aerodynamic force may be assumed to be negligible for relatively short term missions (though a small amount of drag may be present which results in decay of ...
For the Apollo lunar missions, TLI was performed by the restartable J-2 engine in the S-IVB third stage of the Saturn V rocket. This particular TLI burn lasted approximately 350 seconds, providing 3.05 to 3.25 km/s (10,000 to 10,600 ft/s) of change in velocity , at which point the spacecraft was traveling at approximately 10.4 km/s (34150 ft/s ...
The first crewed Apollo missions occurred in 1968. It was also the year in which Earth lifeforms first left low Earth orbit, during the successful Zond 5 mission to the Moon and the Zond 6 lunar mission which crashed upon return, and the year that humans first left low Earth orbit, during the successful Apollo 8 mission to the Moon.
Frank Borman, the commander of NASA’s Apollo 8 voyage into space that orbited humans around the moon for the first time, has died aged 95.. Borman passed away on Tuesday in Billings, Montana ...
Orbit determination has a long history, beginning with the prehistoric discovery of the planets and subsequent attempts to predict their motions. Johannes Kepler used Tycho Brahe's careful observations of Mars to deduce the elliptical shape of its orbit and its orientation in space, deriving his three laws of planetary motion in the process.
Their one-way delta-v budgets from LEO range upwards from 3.8 km/s (12,000 ft/s), which is less than 2/3 of the delta-v needed to reach the Moon's surface. [10] But NEOs with low delta-v budgets have long synodic periods , and the intervals between times of closest approach to the Earth (and thus most efficient missions) can be decades long.