Satellite following circular orbit.

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SUMMARY

The discussion focuses on the calculations involved in determining the gravitational potential energy and kinetic energy of a satellite with a mass of 500 kg in circular orbits around Earth. The satellite transitions from an orbit with a radius of 2re to one with a radius of 3re. Key equations used include the gravitational potential energy formula Ep = -G(mearthmsatellite)/r and the velocity formula v = sqrt(Gmplanet/r). Participants clarify that the radius for calculations should be measured from the center of Earth, emphasizing the importance of distinguishing between radius and altitude.

PREREQUISITES
  • Understanding of gravitational potential energy calculations
  • Familiarity with circular orbital mechanics
  • Knowledge of the gravitational constant (G) and its application
  • Basic principles of energy conservation in physics
NEXT STEPS
  • Study the derivation and application of the gravitational potential energy formula Ep = -G(m1m2)/r
  • Learn about the relationship between kinetic energy and gravitational potential energy in orbital mechanics
  • Research the concept of escape velocity and its derivation from gravitational principles
  • Explore the effects of altitude on gravitational force and orbital speed
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Students studying physics, particularly those focusing on mechanics and gravitational forces, as well as educators looking for examples of orbital dynamics and energy conservation principles.

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Homework Statement


A satellite with a mass of 5.00 x 10^2kg is in a circular orbit, whose radius is 2r_e, around earth. Then it is moved to a circular orbit with a radius of 3r_e.

a) Determine the satellite's gravitational potential energy from the first orbit to the second orbit.
b) Determine the change in gravitational potential energy from the first orbit to the second orbit.
c) Determine the work done in moving the satellite from the first orbit to the second orbit. Apply energy conservation.
d) Calculate the speed it would need in order to maintain its new orbit.
e) Calculate the escape velocity for the satellite if it is on the Earth's surface.


Homework Equations


E_p = -1(G*m_1*m_2)/r
(delta)E_p = -((G*m_1*m_2)/r) - (-((G*m_1*m_2)/r))
v = sqrt((G*m_planet)/r)
v_escape = sqrt((2*G*m_planet)/r)


The Attempt at a Solution


I worked out all the questions but I am wondering about the wording and if I should have considered a few things.

Questions a+b:
For the radius it lists 2r_e that is basically 2*(Radius of earth) correct?
And when calculating the potential gravitational energy, E_p will the radius be (2r_e+Radius of earth)? The question says "whose radius is 2r_e, around Earth" implying that you would add the radius of Earth on top of the multiplication.

So E_p_i = -(G*m_earth*m_satellite)/(2*r_e+r_e)

Question c:
Isn't this just the result of question b?

d+e:
no problems here just plug into the eqn and solve.

Thanks in advance!
 
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Radius means distance from the center. Altitude means height above the surface.
 
D H said:
Radius means distance from the center. Altitude means height above the surface.

Thank you!
 
an orbital radius is typically measured from the center of the object that it is orbiting. if the orbital radius is 2r_e then use 2*(radius of earth) not 3*. I understand your interpretation, but I think it's incorrect.

question c: looks like it to me. your teacher probably wants some statement or equation as proof though.
 
dator said:
Question c:
Isn't this just the result of question b?
No. Question (b) is about gravitational potential energy only. There is also kinetic energy to consider.
 

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