Orbital Period Calculator
Calculate the orbital period of a satellite or planet using Kepler's third law. Astronomy calculator for orbital mechanics, satellite deployment planning, and astrophysics students. Supports circular and elliptical orbits around any celestial body.
Kepler's Third Law
T = 2π√(a³/GM)Variables:
- TOrbital period (seconds)Orbital period (seconds)
- aSemi-major axis (meters)Semi-major axis (meters)
- GGravitational constant (6.674×10⁻¹¹ N·m²/kg²)Gravitational constant (6.674×10⁻¹¹ N·m²/kg²)
- MCentral star/planet mass (kg)Central star/planet mass (kg)
How to Use
- 1
Input Massa
Enter massa bintang/planet pusat (kg).
- 2
Input Sumbu Semi-Mayor
Enter jarak rata-rata orbit a (m).
- 3
Calculate
Dapatkan periode orbit in seconds/days/years.
Examples
Bumi Mengelilingi Matadays
Problem:
M = 1.989×10³⁰ kg, a = 1.496×10¹¹ m. Cari T?
Solution:
- 1.T = 2π√((1.496×10¹¹)³ / (6.674×10⁻¹¹ × 1.989×10³⁰))
- 2.T ≈ 3.156×10⁷ seconds
Result:≈ 365.25 days
Bumi memerlukan 365.25 days for satu orbit mengelilingi Matadays.
Frequently Asked Questions
What is Hukum Kepler 3?
T² ∝ a³, periode kuadrat berbanding lurus with pangkat tiga sumbu semi-mayor.
How with satelit Bumi?
Gunakan M = massa Bumi (5.972×10²⁴ kg) and jarak orbit from pusat Bumi.