Editing Orbital inclination change (section)

== Efficiency ==
The simplest way to perform a plane change is to perform a burn around one of the two crossing points of the initial and final planes. The delta-v required is the vector change in velocity between the two planes at that point.

However, maximum efficiency of inclination changes are achieved at [[apoapsis]], (or [[apogee]]), where orbital velocity <math>v</math> is the lowest. In some cases, it can require less total delta-v to raise the satellite into a higher orbit, change the orbit plane at the higher apogee, and then lower the satellite to its original altitude.<ref name=Braeunig>{{cite web |url=http://www.braeunig.us/space/orbmech.htm#maneuver |title=Basics of Space Flight: Orbital Mechanics |last=Braeunig |first=Robert A |access-date=2008-07-16 |archive-url=https://web.archive.org/web/20120204054322/http://www.braeunig.us/space/orbmech.htm#maneuver |archive-date=2012-02-04 |url-status=dead }}</ref>

For the most efficient example mentioned above, targeting an inclination at [[apoapsis]] also changes the [[argument of periapsis]]. However, targeting in this manner limits the mission designer to changing the plane only along the [[apse line|line of apsides]].{{citation needed|date=February 2011}}

For [[Hohmann transfer orbit]]s, the initial orbit and the final orbit are 180 degrees apart. Because the transfer orbital plane has to include the central body, such as the Sun, and the initial and final nodes, this can require two 90 degree plane changes to reach and leave the transfer plane. In such cases it is often more efficient to use a ''broken plane maneuver'' where an additional burn is done so that plane change only occurs at the intersection of the initial and final orbital planes, rather than at the ends.<ref>{{cite report|title=Broken-Plane Maneuver Applications for Earth to Mars Trajectories|url=http://issfd.org/ISSFD_2007/3-1.pdf|first=Fernando |last=Abilleira|access-date=November 13, 2022}}</ref>