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| Launch at 80 km altitude, 6458 km radius. GM is 3.986e14 m^2^/s^2^, day is 86164 seconds, escape velocity is 11111 m/s. rotation velocity 471 m/s, effective escape 10640 m/s . '''Not including air drag on the way out, which will be significant.''' | Launch at 80 km altitude, 6458 km radius. GM is 3.986e14 m^3^/s^2^, day is 86164 seconds, escape velocity is 11111 m/s. rotation velocity 471 m/s, effective escape 10640 m/s . '''Not including air drag on the way out, which will be significant.''' |
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| || || radius km || launch V || kick V || || ISS || 6780 km || 7480 m/s || 94 m/s || inclination 51.65°, inaccessable from equatorial plane launch || || M288 || 12789 km || 8586 m/s || 1009 m/s || || GEO || 42164 km || 9875 m/s || 1490 m/s || || Moon || 384400 km || 10547 m/s || 833 m/s || Moon's orbit inclined compared to Earth's axial tilt || || Mars || || 11002 m/s || 5630 m/s || sum of squares, eff. escape + 2.86 m/s || |
|| || radius km || launch V || orbit V || kick V ||<-2> delta V/deg plane change from loop latitude || || ISS || 6780 km || 7480 m/s || 7668 m/s || 94 m/s ||134 m/s/° || altitude only, ISS inclination 51.65°, inaccessable || || M288 || 12789 km || 8586 m/s || 5583 m/s || 1009 m/s || 97 m/s/° || || GEO || 42164 km || 9875 m/s || 3075 m/s || 1490 m/s || 54 m/s/° || || Moon || 384400 km || 10547 m/s || 1018 m/s || 833 m/s || 18 m/s/° || Moon's orbit inclined compared to Earth's axial tilt || || Mars || || 11002 m/s || || 5630 m/s || || kick=Mars landing, eff. escape + 2.86 m/s || libreoffice spreadsheet [[attachment:destinations.ods]] |
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Saving perhaps 200 m/s of delta V on a Mars rocket launch is significant. Not for a launch loop. It is more important to save delta V for the kick. |
Launch Loop Destinations
Launch at 80 km altitude, 6458 km radius. GM is 3.986e14 m3/s2, day is 86164 seconds, escape velocity is 11111 m/s. rotation velocity 471 m/s, effective escape 10640 m/s . Not including air drag on the way out, which will be significant.
|
radius km |
launch V |
orbit V |
kick V |
delta V/deg plane change from loop latitude |
|
ISS |
6780 km |
7480 m/s |
7668 m/s |
94 m/s |
134 m/s/° |
altitude only, ISS inclination 51.65°, inaccessable |
M288 |
12789 km |
8586 m/s |
5583 m/s |
1009 m/s |
97 m/s/° |
|
GEO |
42164 km |
9875 m/s |
3075 m/s |
1490 m/s |
54 m/s/° |
|
Moon |
384400 km |
10547 m/s |
1018 m/s |
833 m/s |
18 m/s/° |
Moon's orbit inclined compared to Earth's axial tilt |
Mars |
|
11002 m/s |
|
5630 m/s |
|
kick=Mars landing, eff. escape + 2.86 m/s |
libreoffice spreadsheet destinations.ods
Note that gravity assist from the Moon reduce the Mars launch velocity a tiny bit - but not much, because the vehicle must leave the Moon at precisely the right direction (tangential to Earth's orbit) and velocity ( 2860 m/s added to the Earth's 29,800 m/s solar orbital velocity to be in a Hohmann orbit to Mars, and this must happen at precisely the right window to reach Mars when it gets there. These windows happen every 780 days, and the Moon will be in the wrong place most of those days. The vehicle can take a faster orbit than a Hohmann (with a higher delta V at each end) and accomodate some "wrongness") but not much.
Saving perhaps 200 m/s of delta V on a Mars rocket launch is significant. Not for a launch loop. It is more important to save delta V for the kick.