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Satellite Q's


Mar 29, 2011
Mar 29, 2011
Hi all, im new to the satellite communications engineering and it would be much appreciated if i could get some guidance on the following questions!:D

prove mathematically the truth of the following statement which appears in
the October 1945 paper:
The velocity of 8 km/sec. applies only to the closest possible orbit, one just outside the
atmosphere and the period of revolution would be about 90 minutes.

Show that for the ellipse the differential element of area dA = r^2 dv/2,
where dis the differential of the true anomaly. Using Kepler’s second law,
show that the ratio of the speeds at apoapsis and periapsis (or apogee and
perigee for an earth-orbiting satellite) is equal to
(1 e)/(1 e)

A satellite in polar orbit has a perigee height of 600 km and an apogee
height of 1200 km. Calculate (a) the mean motion, (b) the rate of regression of
the nodes, and (c) the rate of rotation of the line of apsides. The mean radius of
the earth may be assumed equal to 6371 km

A “no name” satellite has the following parameters specified: perigee
height 197 km; apogee height 340 km; period 88.2 min; inclination 64.6°.
Using an average value of 6371 km for the earth’s radius, calculate (a) the
semimajor axis and (b) the eccentricity. (c) Calculate the nominal mean motion
. (d) Calculate the mean motion. (e) Using the calculated value for a,
calculate the anomalistic period and compare with the specified value.
Calculate (f) the rate of regression of the nodes, and (g) the rate of rotation
of the line of apsides.

any guidance will be much appreciated ! ;)


Apr 7, 2012
Apr 7, 2012
Since that is the homework for a chapter in your Satellite Communications book I suspect you might want to review said chapter again, all the answers or at least a big head start are in said chapter or previous chapters...

If you have a specific question someone might help you out with the math, but we are not doing your homework...