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Radius from True Anomaly Calculator













How This Is Calculated


$$ r = \frac{a (1-e^2)}{1 + e cos(\nu)} $$ where:

r   =   Orbital radius at true anomaly   (m)

a   =   Semi-major axis   (AU)

e   =   Orbital eccentricity   (Dimensionless)

ν   =   True anomaly   (rad)


Assumptions


  • The system is treated as a two-body problem.
  • Central body is spherically symmetric.
  • Orbit follows Kepler's laws of motion.
  • Values are instantaneous.
  • Orbital parameters remain constant.

Related Calculators


Newton's Univeral Law of Gravitation Orbital Inclination Orbital Period Orbital Period for Circular Orbits Orbital Velocity