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jeanbeanie
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Homework Statement
Show that a satellite in low-Earth orbit is approximately P = C(1 + 3h/2R_E) where h is the height of the satellite, C is a constant, and R_E is the radius of the earth)
Homework Equations
p=C(1+3H/2R_E)
p2 = (4∏2)/(GM) * a3. (G - gravitational constant, M - mass of the Earth (in this case) and a = semi-major axis)
The Attempt at a Solution
I've been googling this and I seen one person say use Taylor series. We have not touched that so I am pretty sure it isn't how I should be finding this
so the a is equal to the radui of earth, and its high
a=h+R_E
and i can write that as
a=R_E(1+h/R_E)
SO p2 = (4∏2)/(GM) * R_E(1+h/R_E)3.
I just saw in my noes that's if (4∏2)/(GM) can be cancled out if all meaurments are in Au's, years and solars mass.
Then Id get
p2 = R_E(1+h/R_E)3
and p= R_E(1+h/R_E)3/2
Now what?
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