I'm surprised by the larger delta vee for Landis Land than that for escaping the Earth, since the Venerean gravity field is less.
#KSP DELTA V MAP PDF#
I have also written the school asking permission to upload that pdf and make it available for download. Nydoc, I have sent you my copy of that pdf. It takes a little more delta V but is still quite good. So for routes from EML2 I use Farquhar's path to a perigee deep in earth's gravity. Or if it does descend back to the earth, It would take around 4 months to return to a perigee where the Oberth benefit could be enjoyed. It is quite likely the sun would tear the object from earth's influence into a heliocentric orbit. If nudged loose from the moon's influence, an object at EML2 would fly to a 1,800,000 km apogee, beyond SOI. Perigee would be 300 km, just above earth's atmosphere.ĮML2 follows a roughly circular path 450,000 km from earth's center. In any case, it is interesting that to go from EM2 to a Mars transfer orbit, the required delta-v is so small, less than 1 km/s, whereas from LEO it's about 4 km/s.īob, the capture orbits for departure are a best case scenario that would seldom (if ever) occur in the normal course of things.įor arrival, capture they can be used routinely, so long as peri-apsis passes through the upper atmosphere.įollowing Prussing and Conway's method of Sphere of Influence (SOI), earth's SOI would be about 1,000,000 kilometers from earth's center. I would have thought to leave from EM2 would cost less delta-v since it is further out of Earth's gravity well. However, here to go from EM2 to a highly elliptical orbit around Mars is given as. In your "Inflated delta V's" post you gave the delta-v between highly elliptical orbits from Earth to Mars as 1.1 km/s. If you do, please send me a copy at 27, 2013 at 5:00 PM Do you have a copy of Andreas Stock's paper Investigation on Low Cost Transfer Options to the Earth-Moon Libration Point Region? The link appears to be broken now.
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