When a satellite's mass is negligible compared to the central body, the central body's motion is ignored. Satellite orbits are governed by conservation of energy and angular momentum. In a circular orbit, total mechanical energy, gravitational potential energy, kinetic energy, and angular momentum are all constant. In an elliptical orbit, total mechanical energy and angular momentum remain constant, but kinetic energy and gravitational potential energy trade off as the satellite moves closer to or farther from the central body. Gravitational potential energy is defined as U_g = -G m_1 m_2 / r, with zero at infinite separation. Escape velocity is the speed at which total mechanical energy equals zero.
- Circular orbit: Speed, kinetic energy, gravitational potential energy, and angular momentum are all constant throughout the orbit.
- Elliptical orbit: Total mechanical energy and angular momentum are constant; kinetic energy and gravitational potential energy vary as the satellite moves.
- U_g = -G m_1 m_2 / r: Gravitational potential energy; negative and defined as zero at infinite separation.
- Escape velocity: v_esc = sqrt(2GM/r); the speed at which total mechanical energy of the satellite-planet system equals zero.
- Conservation of angular momentum in orbits: A satellite moves fastest at closest approach (periapsis) and slowest at farthest point (apoapsis) to conserve L = rmv sin theta.
A satellite in an elliptical orbit is at its closest point to Earth. Compared to its farthest point, is its speed greater, smaller, or the same? Which conservation law explains this?
| Orbit type | Total mechanical energy | Angular momentum | KE and PE |
|---|
| Circular | Constant | Constant | Both constant |
| Elliptical | Constant | Constant | Both vary (trade off) |