Question

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

Answer 1

Answer:

Assume spherical earth with average radius of 6378 Km unless specified. 1. Determine ... A Satellite is orbiting in an elliptical orbit with apogee height at 20000 Km and perigee height at 400 Km. The ratio of velocity at perigee to that at apogee will be. A. 3.89 ... 6778 Km. The semi major axis can be calculated as r = ra+rp. 2.

Explanation:

Answer 2

Answer:

18000

Explanation:

Major axis distance = max. distance + min. distance

                                = (apogee altitude + radius) + (perigee altitude + radius)

                                = (4100+6400) + (1100+6400)

                                = (10500) + (7500)

                                = 18000