Dictionary Thesaurus Word Dynamo Quotes Reference Translator Spanish

Elliptic orbit

In astrodynamics or celestial mechanics an elliptic orbit is a Kepler orbit with the eccentricity greater than 0 and less than 1. In a gravitational two-body problem with the eccentricity in this range both bodies follow similar elliptic orbits with the same orbital period around their common barycenter. Also the relative position of one body with respect to the other follows an elliptic orbit.

Specific energy of an elliptical orbit is negative. An orbit with an eccentricity of 0 is a circular orbit. Examples of elliptic orbits include: Hohmann transfer orbit, Molniya orbit and tundra orbit.

Velocity

Under standard assumptions the orbital speed (

v,

) of a body traveling along elliptic orbit can be computed from the Vis-viva equation as:

v=sqrt{muleft({2over{r}}-{1over{a}}right)}

Orbital period

Under standard assumptions the orbital period (

T,!

) of a body traveling along an elliptic orbit can be computed as:

T={2piover{sqrt{mu}}}a^{3over{2}}

where:

$mu,$ is standard gravitational parameter,
$a,!$ is length of semi-major axis.

Conclusions:

The orbital period is equal to that for a circular orbit with the orbit radius equal to the semi-major axis ( $a,!$ ),
The orbital period does not depend on the eccentricity (See also: Kepler's third law).

Energy

Under standard assumptions, specific orbital energy (

epsilon,

) of elliptic orbit is negative and the orbital energy conservation equation (the Vis-viva equation) for this orbit can take the form:

{v^2over{2}}-{muover{r}}=-{muover{2a}}=epsilon<0

where:

$v,$ is orbital speed of orbiting body,
$r,$ is radial distance of orbiting body from central body,
$a,$ is length of semi-major axis,
$mu,$ is standard gravitational parameter.

Conclusions:

Specific energy for elliptic orbits is independent of eccentricity and is determined only by semi-major axis of the ellipse.

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

h, = r, v, cos phi

where:

$h,$ is the specific relative angular momentum of the orbit,
$v,$ is orbital speed of orbiting body,
$r,$ is radial distance of orbiting body from central body,
$phi ,$ is the flight path angle

Equation of motion

See orbit equation

Orbital parameters

The state of an orbiting body at any given time is defined by the orbiting body's position and velocity with respect to the central body, which can be represented by the three-dimensional Cartesian coordinates (position of the orbiting body represented by x, y, and z) and the similar Cartesian components of the orbiting body's velocity. This set of six variables, together with time, are called the orbital state vectors. Given the masses of the two bodies they determine the full orbit. The two most general cases with these 6 degrees of freedom are the elliptic and the hyperbolic orbit. Special cases with less degrees of freedom are the circular and parabolic orbit.

Because at least six variables are absolutely required to completely represent an elliptic orbit with this set of parameters, then six variables are required to represent an orbit with any set of parameters. Another set of six parameters that are commonly used are the orbital elements.