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The mean eccentricity of an object is the average eccentricity as a result of perturbations over a given time period. Neptune currently has an instant (current epoch ) eccentricity of 0.011 3 , [ 13 ] but from 1800 to 2050 has a mean eccentricity of 0.008 59 .
is the eccentricity of the central body (e.g., 0.081819 for Earth) is the geodetic latitude (the angle between the normal line of horizontal plane and the equatorial plane) ′ is the geocentric latitude (the angle between the radius and the equatorial plane)
Often called the impact parameter, this is important in physics and astronomy, and measure the distance a particle will miss the focus by if its journey is unperturbed by the body at the focus. [citation needed] The semi-minor axis and the semi-major axis are related through the eccentricity, as follows:
All bounded orbits where the gravity of a central body dominates are elliptical in nature. A special case of this is the circular orbit, which is an ellipse of zero eccentricity. The formula for the velocity of a body in a circular orbit at distance r from the center of gravity of mass M can be derived as follows:
The eccentricity e is defined as: = . From Pythagoras's theorem applied to the triangle with r (a distance FP) as hypotenuse: = + () = () + ( + ) = + = () Thus, the radius (distance from the focus to point P) is related to the eccentric anomaly by the formula
The inclination is one of the six orbital elements describing the shape and orientation of a celestial orbit.It is the angle between the orbital plane and the plane of reference, normally stated in degrees.
Eccentricity (e) — shape of the ellipse, describing how much it is elongated compared to a circle (not marked in diagram). Semi-major axis (a) — half the distance between the apoapsis and periapsis. The portion of the semi-major axis extending from the primary at one focus to the periapsis is shown as a purple line in the diagram; the rest ...
The classical method of finding the position of an object in an elliptical orbit from a set of orbital elements is to calculate the mean anomaly by this equation, and then to solve Kepler's equation for the eccentric anomaly. Define ϖ as the longitude of the pericenter, the angular distance of the pericenter from a reference direction.