18-01-2013, 11:06 AM
Satellite Communication ( EEC-021)
Satellite Communication.docx (Size: 13.55 KB / Downloads: 34)
Q.1: A geostationary satellite moving in equatorial orbit is at a height of 35786 Km from surface of Earth. If radius of earth is 6378 km. Calculate the period of revolution. (Assume constant value as per standards)
Q.2. A satellite is moving in a circular orbit for the period of 1 day. Calculate the radius of orbit.(Assume constant value as per standards).
Q.3. Satellite-1 in an elliptical orbit has orbital semi-major axis is 18000 Km and satellite -2 in elliptical orbit has Semi-major axis is 24000 Km. Determine the relationship between orbital periods.
Q4. A satellite is moving in high eccentric orbit having farthest and closest points as 35000 Km and 500 Km respectively from the surface of earth. Determine the orbital period and velocity at apogee and perigee points. (Assume constant value as per standards).
Q.5 The semi-major and semi-minor axis of an elliptical satellite orbit are 20000 Km and 1600 Km. respectively. Calculate the Apogee and Perigee distance.
Q.6. The sum of Apogee and Perigee distances of a certain elliptical satellite orbit is 50,000 Km and the difference of the apogee and perigee distance is 30000 Km. Determine the Eccentricity (e)