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Physics, 18.10.2019 16:00 elizabethajih99

Consider a spacecraft in an elliptical orbit around the earth. at the low point, or perigee, of its orbit, it is 500 above the earth's surface; at the high point, or apogee, it is 4000 above the earth's surface.. using conservation of angular momentum, find the ratio of the spacecraft's speed at perigee to its speed at apogee..

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Consider a spacecraft in an elliptical orbit around the earth. at the low point, or perigee, of its...
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