(adsbygoogle = window.adsbygoogle || []).push({}); 1. The problem statement, all variables and given/known data

A 600kg satellite moving in a stable circular orbit about the Earth at a height of 4000km (G=6.67x10^-11 NM^2/kg^2, Re=6380km, Me=5.98x10^24kg).

Calculate the speed of the satellite at that height.

Calculate the orbital period (T), the time for one revolution

Calculate the gravity at height h=4000 km.

2. Relevant equations

Gravitational Force: F=Gm1m2/r^2

centripetal acceleration: a= v^2/r

Period (circular motion): T=2(pie)r/v

3. The attempt at a solution

calculated a gravitational force of 2221179013, plugged it into F=ma, which I came out as 2221179013=600a. Got an acceleration of 3701965.021=v^2/r, which came out to v2= 3701965.02*10380. After taking the square root of that, I finished with v=196026.52m/s, which is off from the correct answer which is 6198.9 m/s. Where did I go wrong, how can I take the right steps? Thanks so much.

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# Satellite moving in a stable circular orbit

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