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A satellite orbiting certain planet has apogee R_(1) and perigee equal to R_(2), then find the minimum kinetic energy that should be given to the satellite to enable it to escape the planate. |
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Answer» Solution :`2A=R_(1)+R_2` `a=(R_1+R_2)/(2)` `tau.epsi=-(GMM)/(2a)` `k.epsi."should be given "=|tau.epsi.|` `=("Gmm")/(2a)` `=("Gmm")/(2(R_(1)+R_(2))` |
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