Destination Orbit Plane Change
A launch loop oriented along the 8 degree south latitude line launches into a plane defined by that vector and the center of the Earth. The launch plane rotates, and orbits launched into one plane will need some north/south delta V to transition to a different plane.
The easiest place to change the orbital plane is at the apogee of a Highly Eccentric Earth Orbit (HEEO) such as a Construction Orbit. The apogee velocity of a one day construction orbit is 1021 m/s prograde; changing that to a retrograde orbit requires a delta V of 2042 m/s, and to a polar orbit requires 1444 m/s .
Less delta V is required for a higher orbit with a lower apogee velocity:
period |
apogee |
semimajor |
eccentricity |
apogee |
perigee |
launch |
arrival |
arrival |
s. day |
km |
km |
from apogee |
V m/s |
V m/s |
V m/s |
dV m/s |
time hr |
1 |
75950.34 |
42164.17 |
-0.8013005 |
1021.18 |
9257.46 |
10195.38 |
114.23 |
11.561 |
2 |
125484.89 |
66931.45 |
-0.8748272 |
630.56 |
9444.51 |
10364.29 |
72.94 |
23.421 |
3 |
167032.01 |
87705.01 |
-0.9044752 |
477.45 |
9518.89 |
10430.86 |
55.95 |
35.314 |
4 |
204116.10 |
106247.05 |
-0.9211460 |
392.41 |
9560.46 |
10467.91 |
46.32 |
47.222 |
5 |
238199.56 |
123288.78 |
-0.9320457 |
337.22 |
9587.54 |
10491.99 |
39.99 |
59.139 |
6 |
270068.04 |
139223.02 |
-0.9398232 |
298.02 |
9606.82 |
10509.10 |
35.46 |
71.062 |
7 |
300205.17 |
154291.59 |
-0.9457002 |
268.51 |
9621.36 |
10522.00 |
32.03 |
82.990 |
8 |
328935.36 |
168656.68 |
-0.9503251 |
245.35 |
9632.79 |
10532.12 |
29.32 |
94.922 |
9 |
356489.53 |
182433.77 |
-0.9540765 |
226.60 |
9642.05 |
10540.32 |
27.13 |
106.856 |
perigee is 2000 km altitude, launch and arrival from a 80 km altitude launch loop at 8° S latitude |