Orbital velocity and period are an integral part of space mission design that is affected by key parameters such as the apogee and perigee of the spacecraft's orbit. This orbital mechanics calculator can help you the orbital velocity and period of a spacecraft in any circular or elliptical orbit around the Earth.

Apogee Height

:700.00km

Perigee Height

:700.00km

Radius of Earth

:6378.1

Gravitational Parameter of Earth

:398600.0

Orbital Velocity (Apogee) km/s

:7.50

Orbital Velocity (Perigee) km/s

:7.50

Orbital Period

:1.65hours

Eccentricity

:0.0

Perigee and apogee are terms used in orbital mechanics to describe the closest and farthest points, respectively, between an object and the primary body it orbits. Perigee represents the point of closest proximity, while apogee denotes the farthest distance in the object's orbit.

The **radii of the apogee and the perigee** of the orbit is found using:

RA

:7,078.10km

RP

:7,078.10kmThe semi-major **axis of the orbit** is found using:

Where:

SMA

:7,078.10kmThe **specific energy** of the spacecraft in orbit is found using:

Where:

Specific energy (km2/s2)

:-28.16

The orbital velocity of the spacecraft at any point in the orbit is found using:

Orbital Velocity (Apogee) km/s

:7.50

Orbital Velocity (Perigee) km/s

:7.50The orbital period in hours of the spacecraft is found using:

Orbital Period

:1.65hours