A satellite is in elliptical orbit about the earth (radius =6400 km). At perigee it has an attitude of 1100 km and at the apogee its attitude is 4100 km. The major axis of the orbit is:

Explanation

Given `S_1E = ` Perigee = 1100 km
`S_2E` = Apogee = 4100 km
From fig. (b)
Major axis `2a = S_1E_1 + 2R +S_2E_2`
` = 1100 +2 xx 6400 + 4100 = 18000 km `