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Elliptical orbit trajectory

  1. Dec 4, 2016 #1
    1. The problem statement, all variables and given/known data
    A satellite moves in an elliptic orbit with eccentricity e=1/2 around a planet which it was launched. When it arrives at an apsis( a radial turning point), its velocity is suddenly doubled. Show that the new orbit will be either parabolic or hyperbolic depending on which of the turning points the velocity doubling occurs.

    2. Relevant equations
    if the E<0 and e<1, the orbit is an ellipse
    if E>0 and e>1 the orbit is a hyperbola

    3. The attempt at a solution

    I tried to solve this question, but I got stuck and couldn't get anywhere cause I wasn't sure what to do.
     
  2. jcsd
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