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  2. Orbital period - Wikipedia

    en.wikipedia.org/wiki/Orbital_period

    It may also refer to the time it takes a satellite orbiting a planet or moon to complete one orbit. For celestial objects in general, the orbital period is determined by a 360° revolution of one body around its primary, e.g. Earth around the Sun. Periods in astronomy are expressed in units of time, usually hours, days, or years.

  3. 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]

  4. Earth's orbit - Wikipedia

    en.wikipedia.org/wiki/Earth's_orbit

    One complete orbit takes 365.256 days (1 sidereal year), during which time Earth has traveled 940 million km (584 million mi). [2] Ignoring the influence of other Solar System bodies, Earth's orbit , also called Earth's revolution , is an ellipse with the Earth–Sun barycenter as one focus with a current eccentricity of 0.0167.

  5. Mean anomaly - Wikipedia

    en.wikipedia.org/wiki/Mean_anomaly

    where M 0 is the mean anomaly at the epoch t 0, which may or may not coincide with τ, the time of pericenter passage. 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.

  6. Gaussian gravitational constant - Wikipedia

    en.wikipedia.org/wiki/Gaussian_gravitational...

    It relates the orbital period to the orbit's semi-major axis and the mass of the orbiting body in Solar masses. The value of k historically expresses the mean angular velocity of the system of Earth+Moon and the Sun considered as a two body problem, with a value of about 0.986 degrees per day, or about 0.0172 radians per day.

  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 ...

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  9. Orbital elements - Wikipedia

    en.wikipedia.org/wiki/Orbital_elements

    If the epoch is defined to be at the moment when one of the elements is zero, the number of unspecified elements is reduced to five. (The sixth parameter is still necessary to define the orbit; it is merely numerically set to zero by convention or "moved" into the definition of the epoch with respect to real-world clock time.)