Assuming a spacecraft is in low Earth orbit with an apogee of 400 km and a perigee of 300 km, and is not maneuvers for the purposes of this exercise, what is the minimum delta-v required to maintain a 3:1 ratio between the apogee and perigee? in C++
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C++
🤖 Code Explanation
This code calculates the delta-v required to maintain a 3:1 ratio between the apogee and perigee of a satellite in low Earth orbit.
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