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Homework Statement
A Hohmann transfer orbit is a way of transferring a spacecraft between two planetary
orbits (which we shall assume are circular) by using one half of an elliptical orbit about
the Sun.
A spacecraft is initially moving around the Sun with the orbital speed V1 of
the first planet, at radius R1, and it is to be moved to a radius R2. The orbital speeds of the spacecraft at perihelion (point A) and aphelion (point B) in the
elliptical orbit are vA and vB respectively. Write down the conditions on vA and vB coming
from (i) the conservation of energy and (ii) the conservation of angular momentum, on
the assumption that the gravitational fields of the planets have a negligible effect on the
spacecraft compared to the gravitational field of the Sun.
Hence derive the required to accelerate the spacecraft into the transfer orbit.
Homework Equations
The Attempt at a Solution
i) 0.5(Va)^2 - GM/R1 = 0.5(Vb)^2 - GM/R2
ii) R1*Va=R2*Vb
I don't know where to go from here? Also, sorry if this is in the wrong forum.