Editing Characteristic energy (section)

==Examples==
[[MAVEN]], a [[Mars]]-bound spacecraft, was launched into a trajectory with a characteristic energy of 12.2&nbsp;km<sup>2</sup>/s<sup>2</sup> with respect to the Earth.<ref>[http://www.nasaspaceflight.com/2013/11/atlasv-launch-maven-mars-mission Atlas V set to launch MAVEN on Mars mission], nasaspaceflight.com, 17 November 2013.</ref> When simplified to a [[two-body problem]], this would mean the MAVEN escaped Earth on a hyperbolic trajectory slowly decreasing its speed towards <math>\sqrt{12.2}\text{ km/s} = 3.5\text{ km/s}</math>. However, since the Sun's gravitational field is much stronger than Earth's, the two-body solution is insufficient. The characteristic energy with respect to Sun was negative, and MAVEN – instead of heading to infinity – entered an [[heliocentric orbit|elliptical orbit around the Sun]]. But the maximal velocity on the new orbit could be approximated to 33.5&nbsp;km/s by assuming that it reached practical "infinity" at 3.5&nbsp;km/s and that such Earth-bound "infinity" also moves with Earth's orbital velocity of about 30&nbsp;km/s.

The [[InSight]] mission to Mars launched with a C<sub>3</sub> of 8.19&nbsp;km<sup>2</sup>/s<sup>2</sup>.<ref>{{Cite web |url=https://www.ulalaunch.com/docs/default-source/launch-booklets/mob_insightfinal.pdf |title=InSight Launch Booklet |last=ULA |date=2018 }}</ref> The [[Parker Solar Probe]] (via Venus) plans a maximum C<sub>3</sub> of 154&nbsp;km<sup>2</sup>/s<sup>2</sup>.<ref>{{Cite web|url=http://parkersolarprobe.jhuapl.edu/The-Mission/index.php#Launch |title=Parker Solar Probe: The Mission |author=JHUAPL |website=parkersolarprobe.jhuapl.edu |language=en |access-date=2018-07-22}}</ref>

Typical ballistic C<sub>3</sub> (km<sup>2</sup>/s<sup>2</sup>) to get from Earth to various planets: Mars 8-16,<ref>[https://digitalcommons.usu.edu/smallsat/2022/all2022/257/ ''Delta-Vs and Design Reference Mission Scenarios for Mars Missions'']</ref> Jupiter 80, Saturn or Uranus 147.<ref>NASA studies for Europa Clipper mission</ref> To Pluto (with its orbital inclination) needs about 160–164&nbsp;km<sup>2</sup>/s<sup>2</sup>.<ref>[http://www.boulder.swri.edu/pkb/ssr/ssr-mission-design.pdf ''New Horizons Mission Design'']</ref>