Chapter 8: Problem 2
Perform the integration of Equation 8.38 to obtain Equation 8.39
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Chapter 8: Problem 2
Perform the integration of Equation 8.38 to obtain Equation 8.39
These are the key concepts you need to understand to accurately answer the question.
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Consider a comet moving in a parabolic orbit in the plane of Earth's orbit. If the distance of closest approach of the comet to the Sun is \(\beta r_{E},\) where \(r_{E}\) is the radius of Earth's (assumed) circular orbit and where \(\beta < 1\), show that the time the comet spends within the orbit of Earth is given by $$\sqrt{2(1-\beta)} \cdot(1+2 \beta) / 3 \pi \times 1 \text { year }$$ If the comet approaches the Sun to the distance of the perihelion of Mercury, how many days is it within Earth's orbit?
The minimum and maximum velocities of a moon rotating around Uranus are \(v_{\min }=v-v_{0}\) and \(v_{\max }=v+v_{0} .\) Find the eccentricity in terms of \(v\) and \(v_{0}\)
In section \(8.2,\) we showed that the motion of two bodies interacting only with each other by central forces could be reduced to an equivalent one-body problem. Show by explicit calculation that such a reduction is also possible for bodies moving in an external uniform gravitational field.
Perform an explicit calculation of the time average (i.e., the average over one complete period) of the potential energy for a particle moving in an elliptical orbit in a central inverse-square-law force field. Express the result in terms of the force constant of the field and the semimajor axis of the ellipse. Perform a similar calculation for the kinetic energy. Compare the results and thereby verify the virial theorem for this case.
A spacecraft is being designed to dispose of nuclear waste either by carrying it out of the solar system or crashing into the Sun. Assume that no planetary flybys are permitted and that thrusts occur only in the orbital plane. Which mission requires the least energy? Explain.
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