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A geostationary orbit, also referred to as a geosynchronous equatorial orbit [a] (GEO), is a circular geosynchronous orbit 35,786 km (22,236 mi) in altitude above Earth's equator, 42,164 km (26,199 mi) in radius from Earth's center, and following the direction of Earth's rotation.
Orbit Center-to-center distance Altitude above the Earth's surface Speed Orbital period Specific orbital energy; Earth's own rotation at surface (for comparison— not an orbit) 6,378 km: 0 km: 465.1 m/s (1,674 km/h or 1,040 mph) 23 h 56 min 4.09 sec: −62.6 MJ/kg: Orbiting at Earth's surface (equator) theoretical 6,378 km: 0 km
In the special case of a geostationary orbit, the ground track of a satellite is a single point on the equator. In the general case of a geosynchronous orbit with a non-zero inclination or eccentricity, the ground track is a more or less distorted figure-eight, returning to the same places once per sidereal day. [21]: 122
A geostationary orbit, as viewed from above the North Pole. A satellite whose orbital period is an integer fraction of a day (e.g., 24 hours, 12 hours, 8 hours, etc.) will follow roughly the same ground track every day.
GTO is a highly elliptical Earth orbit with an apogee (the point in the orbit of the moon or a satellite at which it is furthest from the earth) of 42,164 km (26,199 mi), [3] or a height of 35,786 km (22,236 mi) above sea level, which corresponds to the geostationary altitude.
The method shown following is the orbit determination of an orbiting ... Calculate the squared scalar distance of the ... Calculate the velocity vector for the second ...
All bounded orbits where the gravity of a central body dominates are elliptical in nature. A special case of this is the circular orbit, which is an ellipse of zero eccentricity. The formula for the velocity of a body in a circular orbit at distance r from the center of gravity of mass M can be derived as follows:
The engine is then fired again at the lower distance to slow the spacecraft into the lower circular orbit. The Hohmann transfer orbit is based on two instantaneous velocity changes. Extra fuel is required to compensate for the fact that the bursts take time; this is minimized by using high-thrust engines to minimize the duration of the bursts.