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The velocity of a satellite orbiting the Earth is primarily determined by its altitude above the Earth's surface. The higher the satellite, the slower its orbital velocity. This is because the gravitational force decreases with distance from the Earth, requiring less velocity to balance the gravitational pull and maintain a stable orbit.
The orbital velocity \(v\) of a satellite can be calculated using the formula \( v = \sqrt{\frac{GM}{r}} \), where \( G \) is the gravitational constant, \( M \) is the mass of the Earth, and \( r \) is the distance from the center of the Earth to the satellite. This formula derives from equating the gravitational force to the centripetal force required to keep the satellite in orbit.
Satellites in low Earth orbit (LEO), which is typically between 160 km and 2,000 km above the Earth's surface, travel at velocities around 7.8 km/s (approximately 28,000 km/h or 17,500 mph). This high velocity is necessary to counteract the gravitational pull and maintain a stable orbit.
A geostationary satellite orbits at an altitude of approximately 35,786 km above the equator and has an orbital period that matches the Earth's rotation period (24 hours). The velocity of a geostationary satellite is about 3.07 km/s (approximately 11,068 km/h or 6,878 mph), which is much slower than satellites in lower orbits due to the greater distance from the Earth.
Once a satellite is in a stable orbit, its velocity remains constant unless acted upon by external forces such as atmospheric drag (in lower orbits) or thrusters for maneuvering. Satellites can use onboard propulsion systems to change their velocity and alter their orbits for specific missions or to avoid collisions with other space debris.