Couldn't tell you. What I do see is that if we put the Cook into an equatorial orbit (radius 7000 km), it'll only take 3.5 km/s of dV to escape Earth orbit:
Code:
Computing Departure Burn...Done!
Burn Delta-V is 3.5602 km/s.
Burn should be performed at true anomaly of 173.3137 degrees of pre-departure orbit.
Burn Vector is as follows:
--J2000 X Component: -0.39291 km/s
--J2000 Y Component: -3.3516 km/s
--J2000 Z Component: 1.1345 km/s
--V Component: 3.3746 km/s
--N Component: 1.1345 km/s
--C Component: 5.5511e-017 km/s
Hyperbolic Departure Orbital Elements are:
--Semi-major Axis: -59839.1693 km
--Eccentricity: 1.117
--Inclination: 5.9307 deg
--Right Asc of Asc Node: 173.3137 deg
--Argument of Periapse: 0 deg
Constraint Error is 0.
##################################################################
If we place it into a 28.5 degree circular orbit (same 7000 km radius), we get the following:
Code:
Computing Departure Burn...Done!
Burn Delta-V is 6.3602 km/s.
Burn should be performed at true anomaly of 171.9502 degrees of pre-departure orbit.
Burn Vector is as follows:
--J2000 X Component: -0.21482 km/s
--J2000 Y Component: -4.2801 km/s
--J2000 Z Component: 4.6996 km/s
--V Component: 1.5341 km/s
--N Component: 6.1724 km/s
--C Component: 4.9405e-015 km/s
Hyperbolic Departure Orbital Elements are:
--Semi-major Axis: -59839.1693 km
--Eccentricity: 1.117
--Inclination: 7.0681 deg
--Right Asc of Asc Node: 140.2245 deg
--Argument of Periapse: 32.8896 deg
Constraint Error is 0.
##################################################################
It pays to keep the Cook in an equatorial orbit unless its so overpowered that it can stand to lose 3 km/s of dV. But I'd rather launch more rockets to the Cook from Earth for supply and whatnot, and provide the Cook with dV margin. But, as usual, its up to the managers.