- #1
Peter Coe
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Homework Statement
A satellite is in a circular orbit passing over the North and South geographical poles as it orbits the Earth. It has a mass of 2200kg and its orbit height is 870km above the Earth's surface. What is the change in momentum of the satellite from when it passes over the equator heading North, to when it next passes over the equator?[/B]
Homework Equations
m (satellite) = 2.2 x 10^3 kg
M (Earth) = 5.98 x 10^24 kg
R = r(earth) + h(satellite) = 6.37 x 10^6 m + 8.7 x 10^5 m = 7.24 x 10^6 m
G = 6.673 x 10^-11 m^3 kg^-1 s^-2
v = SQR (G)(M)/R
a = v^2/R
F(centripetal) = (m(satellite) x v^2)/r
T = (2pi x R)/v
m(1)v(1)r(1) = m(2)v(2)r(2) due to conservation of angular momentum.
The Attempt at a Solution
So v = 7.424 x 10^3 m/s and a = 7.61 m/s. T = 6.127 x 10^3 s or 1.7 hours. Centripetal force = 1.67 x 10^16 N
And here is where I got stuck. Isn't velocity constant in circular orbit? So why is there a change in momentum? Many thanks in advance.