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  2. Orbital elements - Wikipedia

    en.wikipedia.org/wiki/Orbital_elements

    Orbital elements are the parameters required to uniquely identify a specific orbit. In celestial mechanics these elements are considered in two-body systems using a Kepler orbit . There are many different ways to mathematically describe the same orbit, but certain schemes, each consisting of a set of six parameters, are commonly used in ...

  3. Kepler orbit - Wikipedia

    en.wikipedia.org/wiki/Kepler_orbit

    In celestial mechanics, a Kepler orbit (or Keplerian orbit, named after the German astronomer Johannes Kepler) is the motion of one body relative to another, as an ellipse, parabola, or hyperbola, which forms a two-dimensional orbital plane in three-dimensional space. A Kepler orbit can also form a straight line.

  4. Longitude of the ascending node - Wikipedia

    en.wikipedia.org/wiki/Longitude_of_the_ascending...

    The longitude of the ascending node, also known as the right ascension of the ascending node, is one of the orbital elements used to specify the orbit of an object in space. Denoted with the symbol Ω , it is the angle from a specified reference direction, called the origin of longitude , to the direction of the ascending node (☊), as ...

  5. Orbital mechanics - Wikipedia

    en.wikipedia.org/wiki/Orbital_mechanics

    In perfect two-body motion, these orbital elements would be invariant (just like the Keplerian elements would be). However, perturbations cause the orbital elements to change over time. Hence, the position element is written as x 0 ( t ) {\displaystyle x_{0}(t)} and the velocity element as v 0 ( t ) {\displaystyle v_{0}(t)} , indicating that ...

  6. Mean anomaly - Wikipedia

    en.wikipedia.org/wiki/Mean_anomaly

    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.

  7. Two-body problem - Wikipedia

    en.wikipedia.org/wiki/Two-body_problem

    The most prominent example of the classical two-body problem is the gravitational case (see also Kepler problem), arising in astronomy for predicting the orbits (or escapes from orbit) of objects such as satellites, planets, and stars. A two-point-particle model of such a system nearly always describes its behavior well enough to provide useful ...

  8. Kepler's laws of planetary motion - Wikipedia

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

    Despite being correct in saying that the planets revolved around the Sun, Copernicus was incorrect in defining their orbits. Introducing physical explanations for movement in space beyond just geometry, Kepler correctly defined the orbit of planets as follows: [1] [2] [5]: 53–54 The planetary orbit is not a circle with epicycles, but an ellipse.

  9. Hyperbolic trajectory - Wikipedia

    en.wikipedia.org/wiki/Hyperbolic_trajectory

    Because typically all these variables can be determined accurately, a spacecraft flyby will provide a good estimate of a body's mass. μ = b v ∞ 2 tan ⁡ δ / 2 {\displaystyle \mu =bv_{\infty }^{2}\tan \delta /2} where δ = 2 θ ∞ − π {\displaystyle \delta =2\theta _{\infty }-\pi } is the angle the smaller body is deflected from a ...