In astrodynamics or celestial mechanics a elliptic orbit is an orbit with the eccentricity greater than 0 and less than 1.
Specific energy of an elliptical orbit is negative.
Under standard assumptions the orbital velocity () of a body traveling along elliptic orbit can be computed as:
- Velocity does not depend on eccentricity but is determined by length of semi-major axis (),
- Velocity equation is similar to that for hyperbolic trajectory with the difference that for the latter one is positive.
Under standard assumptions the orbital period () of a body traveling along elliptic orbit can be computed as:
Under standard assumptions, specific orbital energy () of elliptic orbit is negative and the orbital energy conservation equation for this orbit takes form:
Using the virial theorem we find:
- the time-average of the specific potential energy is equal to 2ε
- the time-average of r-1 is a-1
- the time-average of the specific kinetic energy is equal to -ε
Flight path angle
Equation of motion
See orbit equation.
Last updated: 06-02-2005 01:34:38