Magnetosphere
https://ccmc.gsfc.nasa.gov/educational/MagnetosphereWebPage.php
 The bow shock distance drops below 10 Re many times per year.
One Sidereal Day Construction orbit and associated plumes
A 1 sidereal day construction orbit with a perigee radius of 8378 km ( 6378 + 2000 ) and an apogee radius of 75950 km ( 2*42164  8378 ) has an apogee of 11.9 Re. Retrograde plumes for apogee orbit insertion will all orbit above the bow shock (and be exposed to the proton flux of the solar wind) many times per year. Two relevant related orbits will be a launch orbit from a perigee radius of 6458 km, and a HEEO to GEO/Laplace transfer orbit with a perigee radius of 42164 km (Ignoring J₂ gravitational effects):

Radius km 
Velocity km/s 

Orbit 
Perigee 
Apogee 
Semimajor 
Perigee 
Apogee 
Semimajor 
Delta V 
Launch 
6458 
75950 
41204 
10.666 
0.907 
3.110 
10.190 perigee prograde 
Construction HEEO 
8378 
75950 
42164 
9.257 
1.021 
3.075 
0.114 apogee prograde 
GEO Transfer 
42164 
75950 
59057 
3.487 
1.936 
2.598 
0.915 apogee prograde 
GEO 
42164 
42164 
42164 
3.075 
3.075 
3.075 
0.412 perigee retrograde 
A rocket launch plume is almost entirely deposited in the atmosphere (a huge waste of energy and propellant, which is why launch loop is attractive ... if it is practical). No permanent plume problem (except for maneuvering and plane change thrust) so it will not be considered further. The other three Delta V's might cause permanent plume problems, let's find out:
Transfer Plume Velocity Range 
altitude 
escape 
entry 
vmin 
vmax 
maneuver and plume direction 
km 
km/s 
km/s 
km/s 
km/s 
0.114 km/s apogee delta retrograde 
75950 
3.240 
0.907 
0.907 
1.021 
0.915 km/s apogee delta retrograde 
75950 
3.240 
0.907 
1.021 
1.936 
0.412 km/s perigee delta prograde 
42164 
4.348 
1.585 
+3.487 
+3.075 