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← Revision 17 as of 2020-11-12 20:00:52 ⇥
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| ||<9> Mean Free Path Versus Altitude || || Altitude || Temperature || Mean Free Path || Alt || Temp || M.F.P. || Alt || Temp || M.F.P. || || 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 ||| |
=== 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<<BR>>erature || Mean<<BR>>Free<<BR>>Path || . . . ||Altitude || Temp<<BR>>erature || Mean<<BR>>Free<<BR>>Path || . . . || Altitude || Temp<<BR>>erature || Mean<<BR>>Free<<BR>>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 || |
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.
Plume Reentry
Interplanetary spacecraft will be assembled in a one-day HEEO 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).
Mean Free Path Versus Altitude |
||||||||||
Altitude |
Temp |
Mean |
. . . |
Altitude |
Temp |
Mean |
. . . |
Altitude |
Temp |
Mean |
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 |