Calculate Satellite Apogee and Perigee Heights

Calculates the Apogee and Perigee heights of a satellite based on its eccentricity and semimajor axis.

Enter Eccentricity:

Enter Semimajor Axis (km):

Apogee and Perigee:

Apogee and Perigee are terms used in orbital mechanics to describe specific points in a satellite's orbit around the Earth:

• Apogee: This is the highest point in a satellite's orbit above the Earth's surface. It represents the point where the satellite is farthest from the Earth.
• Perigee: This is the lowest point in a satellite's orbit above the Earth's surface. It represents the point where the satellite is closest to the Earth.

These terms are crucial for understanding and analyzing satellite orbits and are often used in satellite mission planning and calculations.

Calculation:

The Apogee height (ha) and Perigee height (hp) are calculated using the following equations:

ha = Semimajor Axis * (1 + Eccentricity) - Mean Earth's Radius

hp = Semimajor Axis * (1 - Eccentricity) - Mean Earth's Radius