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The escape velocity of a satellite circularly orbiting a large body comes from conservation of energy. Are there any modifications that must be made for the escape velocity of an elliptical orbit?
Thanks in advance!
Thanks in advance!
That depends on your definition of "optimal". For rockets the optimal point is characterized by the highest velocity:If I trying to find the optimal point for escape in an elliptical orbit, can I just differentiate the standard escape velocity eqn with respect to r?
You used the wrong expression for orbital velocity.So I tried doing precisely that, I minimized a 'thrust' but the expression I arrive at doesn't look like the perigee....View attachment 68288