# Characteristic energy

In astrodynamics, the **characteristic energy** () is a measure of the excess specific energy over that required to just barely escape from a massive body. The units are length^{2}time^{−2}, i.e. energy per mass.

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

where is the standard gravitational parameter of the massive body with mass and 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 C_{3} is *twice* the specific orbital energy 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:

## Parabolic trajectory

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

## Hyperbolic trajectory

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

where

- is the standard gravitational parameter,
- is the semi-major axis of the orbit's hyperbola (which is negative by convention).

Also:

where is the asymptotic velocity at infinite distance. Spacecraft's velocity approaches 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 km^{2}sec^{−2 }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 But 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 maximum 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.

## See also

## References

- Wie, Bong (1998). "Orbital Dynamics".
*Space Vehicle Dynamics and Control*. AIAA Education Series. Reston, Virginia: American Institute of Aeronautics and Astronautics. ISBN 1-56347-261-9.