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