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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. 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.

  4. Kessler syndrome - Wikipedia

    en.wikipedia.org/wiki/Kessler_syndrome

    The Kessler syndrome is troublesome because of the domino effect and feedback runaway wherein impacts between objects of sizable mass spall off debris from the force of the collision. The fragments can then hit other objects, producing even more space debris: if a large enough collision or explosion were to occur, such as between a space ...

  5. 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.

  6. 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.

  7. 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 ...

  8. Kepler's laws of planetary motion - Wikipedia

    en.wikipedia.org/wiki/Kepler's_laws_of_planetary...

    The important special case of circular orbit, ε = 0, gives θ = E = M. Because the uniform circular motion was considered to be normal, a deviation from this motion was considered an anomaly. The proof of this procedure is shown below.

  9. Geosynchronous orbit - Wikipedia

    en.wikipedia.org/wiki/Geosynchronous_orbit

    A circular geosynchronous orbit has a constant altitude of 35,786 km (22,236 mi). [1] A special case of geosynchronous orbit is the geostationary orbit (often abbreviated GEO), which is a circular geosynchronous orbit in Earth's equatorial plane with both inclination and eccentricity equal to 0. A satellite in a geostationary orbit remains in ...