Editing Geocentric orbit (section)

===Eccentricity classifications===
; [[Circular orbit]] : An orbit that has an [[Orbital eccentricity|eccentricity]] of 0 and whose path traces a circle.
; [[Elliptic orbit]] : An orbit with an [[Orbital eccentricity|eccentricity]] greater than 0 and less than 1 whose orbit traces the path of an [[ellipse]].
:; [[Hohmann transfer orbit]] : An orbital maneuver that moves a spacecraft from one [[circular orbit]] to another using two engine [[impulse (physics)|impulse]]s. This maneuver was named after [[Walter Hohmann]].
:; [[Geosynchronous transfer orbit]] (GTO) : A geocentric-[[elliptic orbit]] where the [[perigee]] is at the altitude of a [[low Earth Orbit]] (LEO) and the [[apogee]] at the altitude of a [[geosynchronous orbit]].
:; [[Highly elliptical orbit]] (HEO) : Geocentric orbit with apogee above 35,786 km and low perigee (about 1,000 km) that result in long dwell times near apogee.
::; [[Molniya orbit]] : A [[highly elliptical orbit]] with [[inclination]] of 63.4° and [[orbital period]] of ½ of a [[sidereal day]] (roughly 12 hours). Such a satellite spends most of its time over a designated area of the Earth.
::; [[Tundra orbit]] : A [[highly elliptical orbit]] with [[inclination]] of 63.4° and [[orbital period]] of one [[sidereal day]] (roughly 24 hours). Such a satellite spends most of its time over a designated area of the Earth.
; [[Hyperbolic trajectory]] : An "orbit" with eccentricity greater than 1. The object's [[velocity]] reaches some value in excess of the [[escape velocity]], therefore it will escape the gravitational pull of the Earth and continue to travel [[infinitely]] with a velocity (relative to Earth) decelerating to some finite value, known as the [[hyperbolic excess velocity]].
:; Escape Trajectory : This trajectory must be used to launch an interplanetary probe away from Earth, because the excess over escape velocity is what changes its [[heliocentric orbit]] from that of Earth.
:; Capture Trajectory : This is the mirror image of the escape trajectory; an object traveling with sufficient speed, not aimed directly at Earth, will move toward it and accelerate. In the absence of a decelerating engine impulse to put it into orbit, it will follow the escape trajectory after periapsis.
; [[Parabolic trajectory]] : An "orbit" with eccentricity exactly equal to 1. The object's [[velocity]] equals the [[escape velocity]], therefore it will escape the gravitational pull of the Earth and continue to travel with a velocity (relative to Earth) decelerating to 0. A spacecraft launched from Earth with this velocity would travel some distance away from it, but follow it around the Sun in the same [[heliocentric orbit]]. It is possible, but not likely that an object approaching Earth could follow a parabolic capture trajectory, but speed and direction would have to be precise.