Solve problem without Lagrange Equations.

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SUMMARY

The discussion centers on a classical mechanics problem involving the stable orientation of a satellite composed of two identical spherical modules connected by a mass-less conduit. The participants initially attempted to solve the problem using Lagrange equations but found the solution lengthy and sought a simpler method. The problem originates from a qualifier exam at the University of Wisconsin and requires calculating the potential energy of the satellite in different orientations relative to Earth's center.

PREREQUISITES
  • Understanding of Newtonian Mechanics
  • Familiarity with potential energy concepts
  • Knowledge of Lagrange equations of motion
  • Basic principles of satellite dynamics
NEXT STEPS
  • Calculate potential energy for various orientations of the satellite
  • Explore alternative methods to solve dynamics problems without Lagrange equations
  • Study the principles of stability in satellite systems
  • Review classical mechanics focusing on energy conservation and equilibrium
USEFUL FOR

This discussion is beneficial for physics students, educators in classical mechanics, and engineers involved in satellite design and dynamics analysis.

Wondering
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A friend and I were debating the solution to this problem, seen below, and cannot solve it without using Lagrange equations but it is suppose to have a solution that is super simple; but we didn't see it.

Anyway, it is a old qualifier question from the Univ. of Wisconsin (open record so anyone can view it). NOTE: This is NOT a homework question NOR will it appear on another qualifier. My friend and I were simply arguing this:

Homework Statement



Suppose the US and Russia were to jointly build a space station with two identical spherical modules (mass, m) to house their crews, and that they are joined by an effectively mass-less conduit (length, d) for astronauts to visit each other. What is the stable orientation of this satellite? (i.e., determine the angle α between the conduit and the line joining the c.m of the satellite and the Earth’s center). Hint: The potential energy of a non-spherical satellite varies slightly, depending on its orientation relative to its orbit.


Homework Equations


Using general Newtonian Mechanics.


The Attempt at a Solution


The solution we got was very lengthy using Lagrange Equations of motion, we are interested in how anyone could do this a "quick way". Note: We both haven't touched classical mechanics in a long time.
 
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Wondering said:
A friend and I were debating the solution to this problem, seen below, and cannot solve it without using Lagrange equations but it is suppose to have a solution that is super simple; but we didn't see it.

Anyway, it is a old qualifier question from the Univ. of Wisconsin (open record so anyone can view it). NOTE: This is NOT a homework question NOR will it appear on another qualifier. My friend and I were simply arguing this:

Homework Statement



Suppose the US and Russia were to jointly build a space station with two identical spherical modules (mass, m) to house their crews, and that they are joined by an effectively mass-less conduit (length, d) for astronauts to visit each other. What is the stable orientation of this satellite? (i.e., determine the angle α between the conduit and the line joining the c.m of the satellite and the Earth’s center). Hint: The potential energy of a non-spherical satellite varies slightly, depending on its orientation relative to its orbit.


Homework Equations


Using general Newtonian Mechanics.


The Attempt at a Solution


The solution we got was very lengthy using Lagrange Equations of motion, we are interested in how anyone could do this a "quick way". Note: We both haven't touched classical mechanics in a long time.

Can you calculate the potential energy of the satellite for horizontal and vertical orientations? What are they?
 

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