Given that, relative to the geocentric equatorial frame, T= -5420.5 1-4314.8j+zk (km) Ve= -0.5516-0.3520-0.4501 k V= (wh

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answerhappygod
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Given that, relative to the geocentric equatorial frame, T= -5420.5 1-4314.8j+zk (km) Ve= -0.5516-0.3520-0.4501 k V= (wh

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Given That Relative To The Geocentric Equatorial Frame T 5420 5 1 4314 8j Zk Km Ve 0 5516 0 3520 0 4501 K V Wh 1
Given That Relative To The Geocentric Equatorial Frame T 5420 5 1 4314 8j Zk Km Ve 0 5516 0 3520 0 4501 K V Wh 1 (16.62 KiB) Viewed 20 times
Given that, relative to the geocentric equatorial frame, T= -5420.5 1-4314.8j+zk (km) Ve= -0.5516-0.3520-0.4501 k V= (where, z can be chosen as an integer number in the following range: -8000<z<-3000), the eccentricity vector, and the satellite is flying towards apogee, calculate the orbital elements (e, i, 22, co and 6)
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