SATELLITE ORBITS & LAUNCH
REVIEW QUESTIONS
1. Explain the Kepler's law of planetary motion and how are they applicable to
the geostationary satellite.
2. What is orbit ? Derive an expression for the equation of satellite orbit.
3. What is meant by look angles ? Explain them with reference to a geostationary
satellite and earth station.
4. Explain briefly the orbital parameters required to determine a satellite's orbit.
5. Explain the concept of earth coverage and slant range for geostationary
satellite. What are the maximum values of these parameter.
6. Explain the concept and significance of station keeping. What are N-S and E-W
station keeping.
7. Explain how a satellite is placed into geostationary orbit from earth ?
8. What is meant by /orbit perturbations ? Explain in brief.
9. Differentiate between geosynchronous and geostationary orbit.
10. Briefly discuss the various types of orbits.
11. List the advantages and disadvantages of geostationary orbit.
12. Briefly discuss, how does the solar eclipse affect the working of a
communication satellite ? Write the month and the duration when the eclipse
effects are maximum.
13. What do you meant by ascending and descending nodes ? In what units
would these be measured ?
14. What do you understand by line of apsides and line of nodes?
16. A satellite is moving in a circular orbit at a height of 322 Km. Determine
(a) Orbital angular velocity in radians per second.
(b) Orbital period in minutes.
(c) Orbital linear velocity.
16. The semimajor axis of the orbit of an earth orbiting satellite is 9500 Km.
Determine the mean anomaly 10 min. after passage of perigee.
17. The satellite orbit has an eccentricity of 0.002 and a semimajor axis of 10,000
Km. Determine the values of
(a) The latus rectum.
(b) Minor axis
(c) Distance between foci
18. An earth station is located at latitude 35o North and longitude 100
Calculate the antenna look angle for a satellite at 67 o W.
o
West.
19. A satellite orbit has an eccentricity of 0.2 and a semi-major axis of 10,000 Km.
Find the values of the semi-minor axis and the distance between foci.
20. Determine the ratio of the orbital period of the two satellites moving in an
elliptical orbit with a semi-major axis equal to 2400 Km and 1800 Km.
21. The semi-major axis and semi-minor axis of an elliptical satellite orbit are
28000 Km and 18000 Km respectively. Determine the apogee and perigee
distances.
22. Determine the orbital eccentricity, semi-major axis and semi-minor axis of an
eccentric elliptical orbit of a satellite with an apogee and perigee points at a
distance of 50,000 Km and 8,000 m.
23. Determine the escape velocity and the velocity at that point on the orbit for an
object to be launched from the surface of a earth from a point where earth's
radius is 6360 Km.
24. A satellite is orbiting in the equatorial plane with a period from perigee to
perigee of 12 hrs. Calculate the semi-major axis if the eccentricity is 0.002 and
earth's radius is 6378 Km.
25. Explain what is meant by apogee and perigee heights. The cosmos 1675
satellite has an apogee height of 39,342 Km and a perigee height
of 613 Km. Determine the semi-major axis and eccentricity of its orbit.
Assume a mean earth's radius is 6371 Km.
26. The farthest and closest points in a satellite elliptical eccentir orbit from earths
surface are 30,000 Km and 150 Km respectively. Determine the orbit eccentricity.
The radius of earth is 6370 Km.
27. Calculate the orbital velocity of a satellite moving in a circular orbit at a
height 200 Km above the surface of earth (G = 6.67 X 10-l1 ~ - m ~ / k ~ M= 5.98
X 1 0 ~ ~ kg, Re = 6370 Km)