Well, first of all, wherever you got this question from has done a really poor job of question-writing. There are a few assorted blunders in the question, both major and minor ones:
-- 22,500 is the altitude of a geosynchronous orbit in miles, not km.
-- That figure of 22,500 miles is its altitude above the surface, not its radius from the center of the Earth.
-- The orbital period of a synchronous satellite has to match the period of the Earth's rotation, and that's NOT 24 hours. It's about 3 minutes 56 seconds less ... about 86,164 seconds.
Here's my solution to the question, using some of the wreckage as it's given, and correcting some of it. If you turn in these answers as homework, they'll be marked wrong, and you'll need to explain where they came from. If that happens, well, serves ya right for turning in somebody else's answers for homework.
The satellite is traveling a circle. The circle's radius is 26,200 miles (not kilometers) from the center of the Earth, so its circumference is (2 pi) x (26,200 miles) = about 164,619 miles.
Average speed = (distance covered) / (time to cover the distance)
it gravitional pull on earth will increased becauste it is compress to a form of moon which is comperatively smaller so the gravitonal pull on per cm of earth will incrased so we can say that there will be change in acceleration due to gravity
