Differences between revisions 3 and 9 (spanning 6 versions)
 ⇤ ← Revision 3 as of 2016-07-25 22:09:43 → Size: 1598 Editor: KeithLofstrom Comment: ← Revision 9 as of 2017-03-01 01:46:47 → ⇥ Size: 2485 Editor: KeithLofstrom Comment: Deletions are marked like this. Additions are marked like this. Line 3: Line 3: 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.''' Line 5: Line 5: || || 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 || '''Note''' Launch altitude may increase to 100 km to reduce drag.|| || radius km ||sem.lat. || launch V || orbit V  || kick V ||<-2> plane change V from loop latitude |||| ISS || 6780 km || 6615 km || 7480 m/s || 7668 m/s || 94 m/s ||134 m/s/° ||altitude only, ISS incl. 51.65°, inaccessable|||| M288 || 12789 km || 8580 km || 8586 m/s || 5583 m/s || 1009 m/s || 97 m/s/° |||| GEO || 42164 km ||11200 km || 9875 m/s || 3075 m/s || 1490 m/s || 54 m/s/° |||| Moon || 384400 km ||12700 km ||10547 m/s || 1018 m/s || 833 m/s||487 m/s max||Moon's orbit inclined compared to Earth's axial tilt|||| Mars || ||12920 km ||11002 m/s || || 5630 m/s ||   || eff. escape + 2.86 m/s, kick= Mars landing || Line 12: Line 14: If the launch loop is placed south of the equator, to avoid January thunderstorms in the intertropical convergence zone (ITCZ), extra delta V will be needed after apogee kick to change orbit inclination into a circular equatorial orbit. The Moon is a special case; since its inclination varies from the Earth's equatorial plane by 23.44±5.14°, the plane change relative to the equator (and relative to a southerly offset loop) will vary. The number given for the Moon is relative to the maximum 28.58°; by launching at the right time of day and month, the loop latitude inclination reduces this.

# 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.

Note Launch altitude may increase to 100 km to reduce drag.

 radius km sem.lat. launch V orbit V kick V plane change V from loop latitude ISS 6780 km 6615 km 7480 m/s 7668 m/s 94 m/s 134 m/s/° altitude only, ISS incl. 51.65°, inaccessable M288 12789 km 8580 km 8586 m/s 5583 m/s 1009 m/s 97 m/s/° GEO 42164 km 11200 km 9875 m/s 3075 m/s 1490 m/s 54 m/s/° Moon 384400 km 12700 km 10547 m/s 1018 m/s 833 m/s 487 m/s max Moon's orbit inclined compared to Earth's axial tilt Mars 12920 km 11002 m/s 5630 m/s eff. escape + 2.86 m/s, kick= Mars landing