Consider a spacecraft in an elliptical örbit áröund thế éärth. t the low point, or perigee, of its orbit, it is 300 km above the earth's surface; at the high point, or apogee, it is 5000 km above the What is the period of the spacecraft's orbit? earth's surface. Express your answer in seconds. ? T = Submit Request Answer Part B Using conservation of angular momentum, find the ratio of the spacecraft's speed at perigee to its speed at apogee. Uperigee Vapogee Submit Request Answer

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11th Edition
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Chapter1: Units, Trigonometry. And Vectors
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Consider a spacecraft in an elliptical orbit around the earth. At the
low point, or perigee, of its orbit, it is 300 km above the earth's
surface; at the high point, or apogee, it is 5000 km above the
earth's surface.
What is the period of the spacecraft's orbit?
Express your answer in seconds.
?
T =
S
Submit
Request Answer
Part B
Using conservation of angular momentum, find the ratio of the spacecraft's speed at perigee to its speed at apogee.
VO AE
Vperigee
Vapogee
Submit
Request Answer
Part C
Using conservation of energy, find the speed at perigee and the speed at apogee.
Enter your answers in meters per second separated by a comma.
Transcribed Image Text:Consider a spacecraft in an elliptical orbit around the earth. At the low point, or perigee, of its orbit, it is 300 km above the earth's surface; at the high point, or apogee, it is 5000 km above the earth's surface. What is the period of the spacecraft's orbit? Express your answer in seconds. ? T = S Submit Request Answer Part B Using conservation of angular momentum, find the ratio of the spacecraft's speed at perigee to its speed at apogee. VO AE Vperigee Vapogee Submit Request Answer Part C Using conservation of energy, find the speed at perigee and the speed at apogee. Enter your answers in meters per second separated by a comma.
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