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This tool applies a standard formula from the relevant domain. The computation is deterministic — given the same inputs, the result is always identical. The formula accounts for the primary variables that determine the output.
T = 2π√(a³/μ) where a = semi-major axis, μ = GMUpdated: July 2026
A typical use case demonstrating the calculator with representative values.
→ Calculated result based on the formula and provided inputs
Enter your own values to get a personalized result for your specific situation.
→ Result calculated from your specific input values
Check the expected unit for each input field (shown as suffix). Converting between imperial and metric units before entering values prevents calculation errors.
Ensure denominator values (divisors) are non-zero. The calculator validates this, but understanding which fields cannot be zero helps interpret results correctly.
Free satellite orbit period calculator using Kepler's third law. Compute orbital period from altitude or semi-major axis for Earth satellites and space. It applies the calculation formula (T = 2π√(a³/μ) where a = semi-major axis, μ = GM). For example: iss altitude ~400 km — A typical use case demonstrating the calculator with representative values.