For a satellite of negligible mass orbiting a massive central body M, gravity provides centripetal force and two conservation laws govern the motion. In circular orbits, total mechanical energy E = -GMm/(2r), kinetic energy K = GMm/(2r), and gravitational potential energy U = -GMm/r are all constant, as is angular momentum L = m v r. In elliptical orbits, total mechanical energy and angular momentum are still conserved, but K and U each vary as the satellite moves closer to or farther from the central body. Escape velocity from radius r is v_esc = sqrt(2GM/r), which corresponds to total mechanical energy equal to zero.
- Circular orbital speed: v_circ = sqrt(GM/r); derived by setting gravitational force equal to centripetal force.
- Total mechanical energy (circular orbit): E = -GMm/(2r); negative value indicates a bound orbit. K = -E and U = 2E.
- Gravitational potential energy: U = -GMm/r; defined as zero at infinite separation, so U is always negative for bound systems.
- Escape velocity: v_esc = sqrt(2GM/r); the minimum speed needed for a satellite to escape to infinity with zero kinetic energy remaining.
- Elliptical orbit conservation: Total mechanical energy and angular momentum L = m v r sin(theta) are constant throughout an elliptical orbit; K and U individually vary.
A satellite in a circular orbit of radius r is given a brief forward thrust that increases its speed. Describe qualitatively what happens to its orbit shape, total energy, and angular momentum immediately after the thrust.
| Orbit type | Total energy E | Angular momentum L | K and U individually |
|---|
| Circular | Constant, -GMm/(2r) | Constant | Both constant |
| Elliptical | Constant (negative) | Constant | Each varies |
| Escape (parabolic) | Zero | Constant | Each varies |