= Interplanetary Launch =
The launch loop is intended for launch velocities below escape, and vehicles of 5 tonnes or less. Interplanetary expeditions will require far more velocity and far larger vehicles. Large interplanetary vehicles will be assembled in orbit from many - perhaps thousands - of 5 tonne components, and fueled for escape (and eventual arrival) with hundreds of additional deliveries of propellant.
MoreLater
=== Plume Reentry ===
Interplanetary spacecraft will be assembled in a one-day [[ HEEO ]] [[ HighApogeeConstruction | construction orbit ]], with apogee at 75950 km radius, and perigee at 8378 km radius (2000 km altitude). A launch loop can launch 5 tonne vehicles and payloads to that high apogee for "kinetic energy cost", proportional to the square of the launch velocity (loop exit velocity added to earth rotation velocity, around 470 m/s at launch loop altitude).
MoreLater
||<-11> '''Mean Free Path Versus Altitude''' ||
|| Altitude || Temp<
>erature || Mean<
>Free<
>Path || . . . ||Altitude || Temp<
>erature || Mean<
>Free<
>Path || . . . || Altitude || Temp<
>erature || Mean<
>Free<
>Path ||
|| km || Kelvin || km || || km || K || km || || km || K || km ||
|| 75 || 208.4 || 9.8E-7 || || 180 || 790.1 || 0.12 || || 500 || 999.2 || 77 ||
|| 80 || 198.6 || 4.4E-6 || || 200 || 854.6 || 0.24 || || 550 || 999.7 || 150 ||
|| 90 || 186.9 || 2.4E-5 || || 250 || 941.3 || 0.89 || || 600 || 999.9 || 280 ||
|| 100 || 195.1 || 1.4E-4 || || 300 || 976.0 || 2.6 || || 700 || 1000 || 730 ||
|| 120 || 360.0 || 3.3E-3 || || 350 || 990.1 || 6.7 || || 800 || 1000 || 1400 ||
|| 140 || 559.6 || 1.8E-2 || || 400 || 995.8 || 16 || || 900 || 1000 || 2100 ||
|| 160 || 626.3 || 5.3E-2 || || 450 || 998.2 || 36 || || 1000 || 1000 || 3100 ||