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  2. Mean anomaly - Wikipedia

    en.wikipedia.org/wiki/Mean_anomaly

    The mean anomaly at epoch, M 0, is defined as the instantaneous mean anomaly at a given epoch, t 0. This value is sometimes provided with other orbital elements to enable calculations of the object's past and future positions along the orbit. The epoch for which M 0 is defined is often determined by convention in a given field or discipline.

  3. Circular orbit - Wikipedia

    en.wikipedia.org/wiki/Circular_orbit

    A circular orbit is depicted in the top-left quadrant of this diagram, where the gravitational potential well of the central mass shows potential energy, and the kinetic energy of the orbital speed is shown in red. The height of the kinetic energy remains constant throughout the constant speed circular orbit.

  4. Mean longitude - Wikipedia

    en.wikipedia.org/wiki/Mean_longitude

    An orbiting body's mean longitude is calculated L = Ω + ω + M, where Ω is the longitude of the ascending node, ω is the argument of the pericenter and M is the mean anomaly, the body's angular distance from the pericenter as if it moved with constant speed rather than with the variable speed of an elliptical orbit.

  5. True anomaly - Wikipedia

    en.wikipedia.org/wiki/True_anomaly

    The true anomaly is usually denoted by the Greek letters ν or θ, or the Latin letter f, and is usually restricted to the range 0–360° (0–2π rad). The true anomaly f is one of three angular parameters (anomalies) that defines a position along an orbit, the other two being the eccentric anomaly and the mean anomaly.

  6. Argument of periapsis - Wikipedia

    en.wikipedia.org/wiki/Argument_of_periapsis

    In the case of circular orbits it is often assumed that the periapsis is placed at the ascending node and therefore ω = 0. However, in the professional exoplanet community, ω = 90° is more often assumed for circular orbits, which has the advantage that the time of a planet's inferior conjunction (which would be the time the planet would ...

  7. Orbital elements - Wikipedia

    en.wikipedia.org/wiki/Orbital_elements

    The mean anomaly changes linearly with time, scaled by the mean motion, [2] =. where μ is the standard gravitational parameter. Hence if at any instant t 0 the orbital parameters are (e 0, a 0, i 0, Ω 0, ω 0, M 0), then the elements at time t = t 0 + δt is given by (e 0, a 0, i 0, Ω 0, ω 0, M 0 + n δt).

  8. Equation of the center - Wikipedia

    en.wikipedia.org/wiki/Equation_of_the_center

    In two-body, Keplerian orbital mechanics, the equation of the center is the angular difference between the actual position of a body in its elliptical orbit and the position it would occupy if its motion were uniform, in a circular orbit of the same period.

  9. Mean motion - Wikipedia

    en.wikipedia.org/wiki/Mean_motion

    In orbital mechanics, mean motion (represented by n) is the angular speed required for a body to complete one orbit, assuming constant speed in a circular orbit which completes in the same time as the variable speed, elliptical orbit of the actual body. [1]