The state vectors for an Earth-orbiting spacecraft at a given point in time are: =(2,200 / +1,300 J+ 6,400 R) km and V = (3.21+5.2J +4.7 R) km/s What is the semi-major axis of the orbit? a. 6,203 km 7,078 km 9,122 km č. d. None of the above 9:-M २६ = -3.986 x 10 k.
The state vectors for an Earth-orbiting spacecraft at a given point in time are: =(2,200 / +1,300 J+ 6,400 R) km and V = (3.21+5.2J +4.7 R) km/s What is the semi-major axis of the orbit? a. 6,203 km 7,078 km 9,122 km č. d. None of the above 9:-M २६ = -3.986 x 10 k.
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Transcribed Image Text:20. The state vectors for an Earth-orbiting spacecraft at a given point in time are:
R=(2,200 / +1,300 / + 6,400 R) km and V= (3.21+5.2 / +4.7 R) km/s
What is the semi-major axis of the orbit?
a.
6,203 km
7,078 km
9,122 km
d. None of the above
a= M = -3.986 x 10 km
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