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Numerical on Hohmann tranfer

  1. Apr 4, 2013 #1
    1. The problem statement, all variables and given/known data

    Consider an initial circular low earth orbit act at a 300 km altitude, find the velocity change required to produce an elliptical orbit with a 300 km altitude at perigee and 3000 km altitude at apogee. Given gravitational parameter for earth μ=398600 kg3/s2, radius of earth R=6378 km.

    3. The attempt at a solution

    The perigee and apogee distance from center of earth is
    rp= 6378+300=6678 km
    ra= 6378+3000=9678 km

    velocity in circular orbit =√(μ/rp)

    angular momentum (H) of elliptical orbit is=√{(2μ*rp*ra/(ra+rp)}

    velocity at perigee = H/rp

    change in velocity (Δv)= [H/rp]- [√(μ/rp)]
     
  2. jcsd
  3. Apr 5, 2013 #2

    SteamKing

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    And ... ?
     
  4. Apr 5, 2013 #3
    I want to know the correct solution to the problem.
     
  5. Apr 5, 2013 #4

    SteamKing

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    Well, you'll have to figure that out for yourself. As has been stated many times before, PF is not a homework service. If you provide an attempt at a solution, members will provide you with hints and feedback.
     
  6. Apr 5, 2013 #5
    Oh sorry, may I know the relevant formulas used by me in the attempt are correct or not?? As I am not getting the correct ans by substituting values to those variables.
     
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