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(II) How much work would be required to move a satellite of mass \(m\) from a circular orbit of radius \(r_{1}=2 r_{\mathrm{E}}\) about the Earth to another circular orbit of radius \(r_{2}=3 r_{\mathrm{E}} ?\) \(\left(r_{\mathrm{E}}\right.\) is the radius of the Earth.)

Short Answer

Expert verified
The required work is \( \frac{G M m}{6 r_E} \)."

Step by step solution

01

Understanding Gravitational Potential Energy

In this problem, we need to calculate the change in gravitational potential energy as the satellite moves from one orbit to another. The gravitational potential energy for an orbit is given by: \( U = -\frac{G M m}{r} \), where \( G \) is the gravitational constant, \( M \) is Earth's mass, \( m \) is the satellite's mass, and \( r \) is the radius of the orbit.
02

Calculate Initial Potential Energy

For the initial orbit at radius \( r_1 = 2 r_E \), the potential energy \( U_1 \) is \( U_1 = -\frac{G M m}{2 r_E} \).
03

Calculate Final Potential Energy

For the final orbit at radius \( r_2 = 3 r_E \), the potential energy \( U_2 \) is \( U_2 = -\frac{G M m}{3 r_E} \).
04

Determine the Change in Potential Energy

The change in potential energy, which is the work done \( W \), is the difference between the final and initial potential energies: \( \Delta U = U_2 - U_1 = \left( -\frac{G M m}{3 r_E} \right) - \left( -\frac{G M m}{2 r_E} \right) \).
05

Simplify the Equation

Simplifying the expression for \( \Delta U \), we get: \[ \Delta U = \frac{G M m}{r_E} \left( \frac{-1}{3} + \frac{1}{2} \right) = \frac{G M m}{r_E} \left( \frac{1}{6} \right) = \frac{G M m}{6 r_E}. \]
06

Conclusion and Final Result

The work required to move the satellite from the initial orbit to the final orbit is given by the change in potential energy: \[ W = \Delta U = \frac{G M m}{6 r_E}. \]

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Key Concepts

These are the key concepts you need to understand to accurately answer the question.

circular orbits
Circular orbits are paths where a satellite or any object moves around a planet in a circular motion, meaning the distance from the satellite to the center of the planet remains constant. This consistency in distance provides a stable orbit where each point along the path has the same gravitational force acting on the satellite." During circular orbit, the gravitational force is balanced by the satellite's inertia, allowing it to maintain its path without spiraling into or away from the planet. In a circular orbit:
  • The gravitational force acts as the centripetal force, keeping the satellite in orbit.
  • The speed of the satellite must be just right to ensure it stays on the circular path.
  • The gravitational potential energy is defined at each point by the distance from the planet.
Understanding these principles is essential to grasp how satellites maintain their positions relative to Earth. In the exercise you're working with, a satellite transitions between two such orbits of different radii, requiring a calculation of the change in gravitational potential energy.
work in gravitational fields
Work in gravitational fields refers to the energy required to move an object within a gravitational field. When dealing with satellites, moving them from one orbit to another involves performing work to overcome the gravitational pull. This work changes the satellite's gravitational potential energy, allowing it to move between orbits.Key points to consider include:
  • Work is calculated as the change in gravitational potential energy when moving between two points in a gravitational field.
  • In the formula for gravitational potential energy, \[ U = -\frac{G M m}{r} \], the negative sign indicates that work must be done against the gravitational field to increase the potential energy.
  • The work required depends on the difference in the radii of the orbits, with larger differences typically requiring more work.
The solution provided in the exercise involves finding this work by calculating the change in potential energy as the satellite moves from one orbit to another. Understanding how work is related to gravitational fields helps one appreciate the energy considerations in satellite motion.
satellite motion
Satellite motion involves understanding the interaction between gravity and a satellite's velocity in keeping it in orbit. Satellites move around Earth because of the gravitational force pulling them towards its center, and their velocity pushing them sideways. Several factors impact satellite motion:
  • The velocity of a satellite must be high enough to counteract the pull of gravity yet not too high to escape the Earth's gravity.
  • Circular orbits are just one type; elliptical orbits involve varying distances from the Earth.
  • Adjustments in velocity or direction often require precise calculations and energy, often done through controlled burns or thruster modifications.
In your specific problem, satellite motion includes moving from a current stable orbit to another, requiring not only an understanding of gravitational forces but also the work needed to change motion. Satellite operators leverage their understanding of these principles to maintain desired orbits and make necessary adjustments.

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Most popular questions from this chapter

(I) Jane, looking for Tarzan, is running at top speed \((5.0 \mathrm{~m} / \mathrm{s})\) and grabs a vine hanging vertically from a tall tree in the jungle. How high can she swing upward? Does the length of the vine affect your answer?

A film of Jesse Owens's famous long jump (Fig. 49) in the 1936 Olympics shows that his center of mass rose 1.1 \(\mathrm{m}\) from launch point to the top of the arc. What minimum speed did he need at launch if he was traveling at 6.5 \(\mathrm{m} / \mathrm{s}\) at the top of the arc?

The Lunar Module could make a safe landing if its vertical velocity at impact is \(3.0 \mathrm{~m} / \mathrm{s}\) or less. Suppose that you want to determine the greatest height \(h\) at which the pilot could shut off the engine if the velocity of the lander relative to the surface is (a) zero; (b) \(2.0 \mathrm{~m} / \mathrm{s}\) downward; (c) \(2.0 \mathrm{~m} / \mathrm{s}\) upward. Use conservation of energy to determine \(h\) in each case. The acceleration due to gravity at the surface of the Moon is \(1.62 \mathrm{~m} / \mathrm{s}^{2}\)

(II) A \(0.40-\mathrm{kg}\) ball is thrown with a speed of \(8.5 \mathrm{~m} / \mathrm{s}\) at an upward angle of \(36^{\circ} .(a)\) What is its speed at its highest point, and \((b)\) how high does it go? (Use conservation of energy.)

Suppose the gravitational potential energy of an object of mass \(m\) at a distance \(r\) from the center of the Earth is given by $$ U(r)=-\frac{G M m}{r} e^{-\alpha r} $$ where \(\alpha\) is a positive constant and \(e\) is the exponential function. (Newton's law of universal gravitation has \(\alpha=0\) ). \((a)\) What would be the force on the object as a function of \(r ?(b)\) What would be the object's escape velocity in terms of the Earth's radius \(R_{\mathrm{E}} ?\)

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