Question

mearth = 5.9742 x 1024 kg

rearth = 6.3781 x 106 m

mmoon = 7.36 x 1022 kg

rmoon = 1.7374 x 106 m

dearth to moon = 3.844 x 108 m (center to center)

G = 6.67428 x 10-11 N-m2/kg2

103 kg satellite is orbitting the earth in a circular orbit with an altitude of 1500 km.

1) How much energy does it take just to get it to this altitude?

2) How much kinetic energy does it have once it has reached this altitude?

3) What is the ratio of the this change in potential energy to the change in kinetic energy? (i.e. what is (a)/(b)?)

4) What would this ratio be if the final altitude of the satellite were 4400 km?

5) What would this ratio be if the final altitude of the satellite were 3185 km?

Fully worked please.

Answer #1

mearth = 5.9742 x 1024 kg
rearth = 6.3781 x 106 m
mmoon = 7.36 x 1022 kg
rmoon = 1.7374 x 106 m
dearth to moon = 3.844 x 108 m (center to
center)
G = 6.67428 x 10-11 N-m2/kg2
A 1200 kg satellite is orbitting the earth in a circular orbit
with an altitude of 1600 km.
1)
How much energy does it take just to get it to this
altitude?
2)
How much kinetic energy does it...

mearth = 5.9742 x 1024 kg
rearth = 6.3781 x 106 m
mmoon = 7.36 x 1022 kg
rmoon = 1.7374 x 106 m
dearth to moon = 3.844 x 108 m (center to
center)
G = 6.67428 x 10-11 N-m2/kg2
A 1900 kg satellite is orbitting the earth in a circular orbit
with an altitude of 1400 km.
1)
How much energy does it take just to get it to this
altitude?
J
2)
How much kinetic energy does...

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rearth = 6.3781 x 106 m
mmoon = 7.36 x 1022 kg
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