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Lunar orbit transfer

  1. Oct 16, 2009 #1
    1. The problem statement, all variables and given/known data
    A spacecraft is inserted into a lunar orbit. It varied from 101.5 km to 11,741,8 km above the surface of the moon. Later it was transferred into a circular orbit 96.6 km above the moon. Compute the delta v total for a 2 maneuver sequence to transfer the spacecraft from the initial orbit into the required circular orbit.


    2. Relevant equations
    Hohmann transfer equations
    delta v total=delta v1+delta v2 which includes ra, rp, mu


    3. The attempt at a solution
    rp=101.5 km + 1738 km
    ra=11741.8 km + 1738 km
    where 1738 km is the radius of the moon
    GM=mu moon=4.902794e3 km^3/s^2
     
  2. jcsd
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