Magnitude of acceleration given the orbit

1. The problem statement, all variables and given/known data
A satellites are placed in a circular orbit that is 3.22 × 105 m above the surface of the earth. What is the magnitude of the acceleration due to gravity at this distance?

2. Relevant equations
a = MG/R^2

3. The attempt at a solution
For the above formula I have trouble because I do not know the mass of the satellite. I end up with

a = M (6.67 x 10^-11)/(6.38 x 10^6 + 3.22 x 10^5)^2

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