The minimum energy required to launch a satellite of mass $m$ from the surface of a planet of mass $M$ and radius $R$ in a circular orbit at an altitude of $2 R$ is
- A$\frac{5 \mathrm{GMm}}{6 \mathrm{R}}$
- B$\frac{2 \mathrm{GMm}}{3 \mathrm{R}}$
- C$\frac{\mathrm{GMm}}{2 \mathrm{R}}$
- D$\frac{\mathrm{GMm}}{3 \mathrm{R}}$
✓ Correct answer: A
Want the full step-by-step reasoning?