Calculating Velocity Change for Hohmann Transfer Orbit

[godhilu]

Homework Statement

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.

The Attempt at a Solution

The perigee and apogee distance from center of Earth is
r_p= 6378+300=6678 km
r_a= 6378+3000=9678 km

velocity in circular orbit =√(μ/r_p)

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

velocity at perigee = H/r_p

change in velocity (Δv)= [H/r_p]- [√(μ/r_p)]

 

[SteamKing]

And ... ?

 

[godhilu]

I want to know the correct solution to the problem.

 

[SteamKing]

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.

 

[godhilu]

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.