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March 27, 2017

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A satellite in an elliptical orbit has a speed of 9.00km/s when it is at its closes approach to the Earth(perigee). The satellite is 7.00x10^6 m from the center of the Earth at this time. When the satellite is at its greatest distance from the center of the Earth (apogee), its speed is 3.66km/s. Find the distance from the satellite to the center of the Earth at apogee. (assume any energy losses are negligible.)

  • College Physics - ,

    Post your work thus far and I'll continue/correct/guide

  • College Physics - ,

    Kfinal + Ugravfinal = Kinitial + Ugravinitial
    which i ended up with
    Vfinal^2 + [2GM/r] = Vinitial^2 + [2GM/r]

    I believe I need to solve for r but this is where I got stuck.

  • College Physics - ,

    Well since it's an elliptical orbit you can set them the distances as functions of Kvff^3

    <Kf^3>(2GM^4)=vf%
    vf%<6.76[FL(3.33/Ki)]=d%
    d%=<4.1882[Ug]
    d=(1.333<pi^4>)(d%)

    Tell me what you get

  • College Physics - ,

    Quick explanation because I have to go;
    Kvff^3
    Rearrange values so that kf^3=vf%
    vf% is of 6.76 because of orbit while 3.33 is the continual. Solve for d%
    d% the continual converted to elliptical motion is going to be roughly 4.1882 (4.188? I believe it's two, but shouldn't matter)
    By Ugravinitial
    and you have d when you apply the standard orbital motion functions.

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