Calculate orbital period, semi-major axis, or central mass using Kepler's Third Law. Covers planets, moons, exoplanets, and artificial satellites.
Kepler's Third Law Calculator computes the relationship between an orbiting body's period and its semi-major axis. Enter any two of the three key variables - orbital period, semi-major axis, or central body mass - and the calculator solves for the third. It is useful when you want to turn an orbit description into a period or distance without working through the algebra yourself.
Kepler's Third Law states that the square of the orbital period is proportional to the cube of the semi-major axis: T² ∝ a³. Newton generalized this to T² = 4π²a³ / (G × M), where G is the gravitational constant and M is the central body's mass. This elegant relationship governs everything from the Moon's 27-day orbit to exoplanets discovered thousands of light-years away.
Use the built-in presets for solar system planets, major moons, and common satellite orbits. The calculator also computes orbital velocity, escape velocity, and gravitational acceleration at the orbital distance, making it a quick reference for classroom work, orbit comparison, and satellite planning.
Use this calculator when you need to solve orbital period, distance, or mass from a simple two-body setup. It is useful for homework, satellite planning, exoplanet work, and quick comparisons between different orbital systems when you want the math in one place instead of piecing it together by hand. That makes it easier to compare orbits that share the same central body without re-deriving the law each time.
Kepler's Third Law (Newton's form): T² = 4π²a³ / (G × M). Where T = orbital period (s), a = semi-major axis (m), G = 6.674 × 10⁻¹¹ N·m²/kg², M = central body mass (kg). Orbital velocity: v = 2πa / T. Escape velocity: v_esc = √(2GM / a).
Result: 365.25 days
Earth orbits at 1 AU (1.496 × 10¹¹ m) around the Sun (1.989 × 10³⁰ kg). Kepler's law yields T ≈ 3.156 × 10⁷ seconds = 365.25 days, matching Earth's known orbital period.
Johannes Kepler published three laws between 1609 and 1619 that describe how planets move around the Sun. The First Law states orbits are ellipses with the Sun at one focus. The Second Law (equal areas) says a planet sweeps out equal areas in equal times. The Third Law — T² ∝ a³ — is the most quantitatively useful.
Isaac Newton proved all three laws follow from his law of universal gravitation and second law of motion. Newton's generalization added the mass term, making Kepler's Third Law applicable to any orbiting system, not just our solar system.
Kepler's Third Law is the primary tool for measuring masses in astronomy. By observing a moon's orbit around a planet, we calculate the planet's mass. Binary star periods and separations yield stellar masses. Exoplanet transit timing gives orbital periods, and combined with radial velocity measurements, reveals both the semi-major axis and the host star's mass.
Space engineers use Kepler's Third Law to design orbits for specific purposes. Communication satellites need geostationary orbits (period = 24 hours). GPS satellites orbit at ~20,200 km altitude (12-hour period). Low-Earth observation satellites orbit at 400-800 km (90-100 minute periods). The calculator lets you explore these relationships interactively.
Kepler's Third Law states that the square of an orbit's period is proportional to the cube of its semi-major axis. For any two objects orbiting the same body, (T₁/T₂)² = (a₁/a₂)³. Newton later showed the proportionality constant depends on the central mass: T² = 4π²a³/(GM).
Yes. The semi-major axis (half the long axis of the ellipse) determines the orbital period regardless of eccentricity. A highly elliptical comet with the same semi-major axis as a circular orbit has the same period.
Technically it does: the full equation uses (M + m). But for planets orbiting stars, m << M, so the planet's mass is negligible. For binary star systems or very large moons, both masses matter.
In SI: period in seconds, semi-major axis in meters, and mass in kilograms. For solar-system work, a convenient form is T in years and a in AU, where T² = a³ for Sun-orbiting bodies. The calculator handles unit conversions automatically, so you can work in the units that match your problem.
Very accurate for two-body problems. Deviations arise from: gravitational perturbations by other bodies, relativistic effects near massive objects, and non-spherical mass distributions. For solar system planets, accuracy is better than 0.01%.
Absolutely. Low Earth Orbit (LEO) at 400 km altitude has a ~92-minute period. Geostationary orbit at 35,786 km has exactly 24 hours. The calculator includes common satellite orbit presets.