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  2. Orbital eccentricity - Wikipedia

    en.wikipedia.org/wiki/Orbital_eccentricity

    Over hundreds of thousands of years, the eccentricity of the Earth's orbit varies from nearly 0.003 4 to almost 0.058 as a result of gravitational attractions among the planets. [4] Luna's value is 0.054 9, the most eccentric of the large moons in the Solar System.

  3. Eccentric anomaly - Wikipedia

    en.wikipedia.org/wiki/Eccentric_anomaly

    The eccentric anomaly E is related to the mean anomaly M by Kepler's equation: [3] = ⁡ This equation does not have a closed-form solution for E given M. It is usually solved by numerical methods, e.g. the Newton–Raphson method. It may be expressed in a Fourier series as

  4. 2006 QH181 - Wikipedia

    en.wikipedia.org/wiki/2006_QH181

    Diagram of 2006 QH 181 's orbit. 2006 QH 181 orbits the Sun beyond Neptune with an orbital period of 541 years. It has an highly elliptical orbit with a semi-major axis of 66.4 astronomical units (AU) and an orbital eccentricity of 0.42. In its eccentric orbit, 2006 QH 181 comes within 38.8 AU from the Sun at perihelion and 94.0 AU at aphelion.

  5. Equation of the center - Wikipedia

    en.wikipedia.org/wiki/Equation_of_the_center

    However, the actual solution, assuming Newtonian physics, is an elliptical orbit (a Keplerian orbit). For these, it is easy to find the mean anomaly (and hence the time) for a given true anomaly (the angular position of the planet around the sun), by converting true anomaly f {\displaystyle f} to " eccentric anomaly ":

  6. Universal variable formulation - Wikipedia

    en.wikipedia.org/wiki/Universal_variable_formulation

    A common problem in orbital mechanics is the following: Given a body in an orbit and a fixed original time , find the position of the body at some later time . For elliptical orbits with a reasonably small eccentricity, solving Kepler's Equation by methods like Newton's method gives excellent results.

  7. Orbital mechanics - Wikipedia

    en.wikipedia.org/wiki/Orbital_mechanics

    From a circular orbit, thrust applied in a direction opposite to the satellite's motion changes the orbit to an elliptical one; the satellite will descend and reach the lowest orbital point (the periapse) at 180 degrees away from the firing point; then it will ascend back. The period of the resultant orbit will be less than that of the original ...

  8. Orbital state vectors - Wikipedia

    en.wikipedia.org/wiki/Orbital_state_vectors

    The body does not actually have to be in orbit for its state vectors to determine its trajectory; it only has to move ballistically, i.e., solely under the effects of its own inertia and gravity. For example, it could be a spacecraft or missile in a suborbital trajectory. If other forces such as drag or thrust are significant, they must be ...

  9. Kepler's laws of planetary motion - Wikipedia

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

    According to Copernicus: [3] [4] The planetary orbit is a circle with epicycles. The Sun is approximately at the center of the orbit. The speed of the planet in the main orbit is constant. Despite being correct in saying that the planets revolved around the Sun, Copernicus was incorrect in defining their orbits.