A) \[\sqrt{2}\]E
B) 2 E
C) E/\[\sqrt{2}\]
D) E
Correct Answer: D
Solution :
When a satellite is orbittmg close to earth, its orbital velocity, \[{{v}_{o}}=\sqrt{\frac{GM}{R}}\] Escape velocity, \[{{v}_{e}}=\sqrt{\frac{2GM}{R}}\] Here, kinetic energy, \[E=\frac{1}{2}mv_{o}^{2}=\frac{1}{2}m\frac{GM}{R}\] KE required to escape, \[{{E}_{1}}=\frac{1}{2}mv_{e}^{2}=\frac{1}{2}m\left( \frac{2GM}{R} \right)=2E\] \[\therefore \] Additional KE required \[=\text{ }2E-E=E\]You need to login to perform this action.
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