A frozen orbit is a special type of nearβcircular orbit in which the perturbations caused by the Earth’s oblateness (the Jβ term) are balanced, preventing the argument of perigee from drifting over time. This stability is crucial for missions that require a fixed ground track, such as Earthβobservation satellites.
The eccentricity required to achieve a frozen condition depends on the semiβmajor axis, the inclination of the orbit, the Earth’s equatorial radius, and the Jβ coefficient. By selecting the appropriate eccentricity, the secular variations in the orbital elements caused by the planetβs nonβspherical gravity field can be nullified.
For a simple analytical approximation, the frozenβorbit eccentricity (e_f) can be expressed as:
What is a frozen orbit?
Why is eccentricity important for a frozen orbit?
How does inclination affect a frozen orbit?
What is the Jβ coefficient in this context?
Can any satellite use a frozen orbit?
How do I input the semi-major axis into the calculator?
What is the significance of the Earth’s equatorial radius in this calculation?
Results are for informational purposes only and do not constitute professional advice.
