Editing Polar orbit (section)

{{short description|Satellite orbit with high inclination}}
[[File:Polar orbit.ogv|thumb|200px|Polar orbit]]
A '''polar orbit''' is one in which a [[satellite]] [[pass (spaceflight)|pass]]es above or nearly above both [[Poles of astronomical bodies|poles]] of the body being [[orbit]]ed (usually a planet such as the [[Earth]], but possibly another body such as the [[Moon]] or [[Sun]]) on each revolution. It has an [[inclination]] of about 80–90 [[Degree (angle)|degree]]s to the body's [[equator]].<ref name="esa">{{cite web |url = http://www.esa.int/Enabling_Support/Space_Transportation/Types_of_orbits |title=ESA - Types of Orbits |date=2020-03-30 |access-date=2021-01-10}}</ref>

Launching [[satellite]]s into polar orbit requires a larger [[launch vehicle]] to launch a given payload to a given altitude than for a [[near-equatorial orbit]] at the same altitude, because it cannot take advantage of the [[Earth's rotation]]al [[velocity]]. Depending on the location of the [[Spaceport|launch site]] and the [[Orbital_inclination|inclination]] of the polar orbit, the launch vehicle may lose up to 460 m/s of [[Delta-v]], approximately 5% of the Delta-v required to attain [[Low Earth orbit]].