For an earth-orbiting satellite, the orbital elements are: h= 79,000km2/s, e= 0.6, N = 50°, i = 110°, w = 15°, and 0 = 40°. Find the state vectors in the geocentric equatorial frame. а. b. What is the radius and velocity at perigee?
For an earth-orbiting satellite, the orbital elements are: h= 79,000km2/s, e= 0.6, N = 50°, i = 110°, w = 15°, and 0 = 40°. Find the state vectors in the geocentric equatorial frame. а. b. What is the radius and velocity at perigee?
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Transcribed Image Text:2. For an earth-orbiting satellite, the orbital elements are: h= 79,000km2/s, e = 0.6, N = 50°, i =
110°, w = 15°, and 0 = 40°.
a. Find the state vectors in the gencentric equatorial frame.
b. What is the radius and velocity at perigee?
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