Satellite Orbiting Earth Energy

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Homework Help Overview

The discussion revolves around calculating the energy required to move a satellite from one circular orbit to another at a higher altitude above Earth. The subject area includes gravitational potential energy and orbital mechanics.

Discussion Character

  • Mathematical reasoning, Assumption checking

Approaches and Questions Raised

  • The original poster attempts to apply gravitational potential energy equations to find the energy difference between two orbits. Some participants question the calculations related to the energy difference and the application of the equations.

Discussion Status

The discussion has seen some productive exchanges, with one participant confirming the method while another has identified a potential error in the original poster's calculations. There is an indication of progress as the original poster acknowledges a mistake in their approach.

Contextual Notes

The original poster's calculations are based on specific gravitational equations, and there is a focus on ensuring the final answer is expressed in megajoules (MJ). The discussion reflects an ongoing exploration of the correct application of these equations.

blackheart
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1. A 962kg satellite orbits the Earth at a constant altitude of 99km. How much energy must be added to the system to move the satellite into a circular orbit with altitude 195km?

2. Homework Equations :

E = (-GMm)/2r
\Delta E = Ef - Ei

3. My work (which produced the wrong answer)...

Ei = (-GMEms)/(2(rE + 99000m))

Ef = (-GMEms)/(2r(E + 195000m))

\Delta E = ((-GMEms)/2)((1/rf)-(1/ri)

The answer needs to be in MJ. I got 858MJ which is incorrect.
 
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Hi blackheart. The method looks good. I got about half your answer.
Did you get 2.26 x 10^-9 for the difference between the 1/r terms?
 
Oh! I didn't divide by two... I have it now. Thanks a bunch.
 
Most welcome.
 

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