smaxemow said:
Satellite velocity in a stable orbit is the speed at which a satellite must travel in order to maintain a stable position in its orbit around a celestial body, such as the Earth. It is influenced by the gravitational pull of the celestial body and the centripetal force needed to keep the satellite in orbit.
The formula for calculating satellite velocity in a stable orbit is v = √(GM/r), where v is the velocity, G is the gravitational constant, M is the mass of the celestial body, and r is the distance between the satellite and the center of the celestial body. This is known as the circular orbit velocity formula.
The main factors that affect satellite velocity in a stable orbit are the mass of the celestial body, the distance between the satellite and the celestial body, and the altitude of the satellite's orbit. Other factors that may influence the velocity include atmospheric drag, solar radiation, and gravitational pull from other celestial bodies.
Geostationary and geosynchronous orbits are both circular orbits around the Earth, but they have different characteristics. A geostationary orbit is one in which the satellite remains in a fixed position above a specific location on the Earth's equator, while a geosynchronous orbit is one in which the satellite completes one orbit around the Earth in the same amount of time as the Earth's rotation. This results in the satellite appearing to be stationary from the Earth's surface.
Calculating satellite velocity in a stable orbit is crucial for the successful deployment and operation of satellites. It ensures that the satellite remains in its designated orbit and does not drift off course. Additionally, knowing the velocity can help determine the amount of fuel required for the satellite to maintain its orbit, as well as the amount of time it will take to complete one orbit.