# Characteristic energy

In astrodynamics, the characteristic energy (${\displaystyle C_{3}}$) is a measure of the excess specific energy over that required to just barely escape from a massive body. The units are length2time−2, i.e. velocity squared or twice the energy per mass.

Every object in a 2-body ballistic trajectory has a constant specific orbital energy ${\displaystyle \epsilon }$ equal to the sum of its specific kinetic and specific potential energy:

${\displaystyle \epsilon ={\frac {1}{2}}v^{2}-{\frac {\mu }{r}}={\text{constant}}={\frac {1}{2}}C_{3},}$

where ${\displaystyle \mu =GM}$ is the standard gravitational parameter of the massive body with mass ${\displaystyle M}$, and ${\displaystyle r}$ is the radial distance from its center. As an object in an escape trajectory moves outward, its kinetic energy decreases as its potential energy (which is always negative) increases, maintaining a constant sum.

Note that C3 is twice the specific orbital energy ${\displaystyle \epsilon }$ of the escaping object.

## Non-escape trajectory

A spacecraft with insufficient energy to escape will remain in a closed orbit (unless it intersects the central body), with

${\displaystyle C_{3}=-{\frac {\mu }{a}}<0}$

where

${\displaystyle \mu =GM}$  is the standard gravitational parameter,
${\displaystyle a}$  is the semi-major axis of the orbit's ellipse.

If the orbit is circular, of radius r, then

${\displaystyle C_{3}=-{\frac {\mu }{r}}}$

## Parabolic trajectory

A spacecraft leaving the central body on a parabolic trajectory has exactly the energy needed to escape and no more:

${\displaystyle C_{3}=0}$

## Hyperbolic trajectory

A spacecraft that is leaving the central body on a hyperbolic trajectory has more than enough energy to escape:

${\displaystyle C_{3}={\frac {\mu }{|a|}}>0}$

where

${\displaystyle \mu =GM}$  is the standard gravitational parameter,
${\displaystyle a}$  is the semi-major axis of the orbit's hyperbola (which may be negative in some convention).

Also,

${\displaystyle C_{3}=v_{\infty }^{2}}$

where ${\displaystyle v_{\infty }}$  is the asymptotic velocity at infinite distance. Spacecraft's velocity approaches ${\displaystyle v_{\infty }}$  as it is further away from the central object's gravity.

## Examples

MAVEN, a Mars-bound spacecraft, was launched into a trajectory with a characteristic energy of 12.2 km2/s2 with respect to the Earth.[1] When simplified to a two-body problem, this would mean the MAVEN escaped Earth on a hyperbolic trajectory slowly decreasing its speed towards ${\displaystyle {\sqrt {12.2}}{\text{ km/s}}=3.5{\text{ km/s}}}$ . 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 elliptical orbit around the Sun. But the maximal velocity on the new orbit could be approximated to 33.5 km/s by assuming that it reached practical "infinity" at 3.5 km/s and that such Earth-bound "infinity" also moves with Earth's orbital velocity of about 30 km/s.

The InSight mission to Mars launched with a C3 of 8.19 km2/s2.[2] The Parker Solar Probe (via Venus) plans a maximum C3 of 154 km2/s2.[3]

C3 (km2/s2) from earth to get to various planets : Mars 12, Jupiter 80, Saturn or Uranus 147.[4] To Pluto (with its orbital inclination) needs about 160-164 km2/s2.[5]