Universal and Gravitational Force

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In an elliptical orbit, the total energy of a satellite remains constant at both perigee and apogee, assuming no friction. The total energy of a satellite in a higher orbit, such as 160 km, is greater than that in a lower orbit, like 144 km, due to weaker gravitational pull at higher altitudes. To compare total energies, one can calculate kinetic energy using Newton's laws and potential energy with the formula PE = -GMm/r. The differences in total energy arise from variations in gravitational force and orbital radius. Understanding these principles is crucial for analyzing satellite orbits.
Neerolyte
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i have a couple questions to ask

1: When a satellite is in eclipsical orbit, the total energy should stay the same wether it is at Perigee or Apogee, neglicting friction, correct?

2: Which is larger - The total energy of the 2.00kg satellite in its 160km orbit or the total energy is its 144km orbit. Why the two answers are different?
 
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1: Pretty much, It depends on how eliptical the orbit is.
2: Well, of course the 160 km orbit, because Earth's pull is weaker.
 
Neerolyte said:
1: When a satellite is in eclipsical orbit, the total energy should stay the same wether it is at Perigee or Apogee, neglicting friction, correct?
That is correct. Total energy (KE + PE) is constant.

2: Which is larger - The total energy of the 2.00kg satellite in its 160km orbit or the total energy is its 144km orbit. Why the two answers are different?
The satellite in higher orbit has greater energy. To understand why, figure it out! Assume a circular orbit: use Newton's 2nd law for centripetal motion to find the speed and thus the KE. The PE = -GMm/r. Now find the total energy for both orbits and compare.
 

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