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Satellite orbital period (Kepler third law) depends on orbital radius and central body mass: T² ∝ a³.
Fórmula
Apply T = 2π√(a³/GM)
- T
- 2π√(a³/GM) — 2π√(a³/GM)
- GM
- GM value — Variable used in the calculation
Guía paso a paso
- 1Input orbital radius or planet name with altitude
- 2Apply T = 2π√(a³/GM)
- 3Results show period in hours/days
Ejemplos resueltos
Entrada
ISS at 400 km altitude around Earth
Resultado
T ≈ 90 minutes
16 orbits per day
Errores comunes a evitar
- ✕Confusing orbital radius with altitude
- ✕Forgetting Earth radius in altitude conversion
Preguntas frecuentes
Does satellite speed change with altitude?
Yes, inverse √r relationship; lower orbits faster.
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