The orbit time of a satellite is calculated using the formula T = 2π√(a^3/GM), where T is the orbit time, a is the semi-major axis of the orbit, G is the gravitational constant, and M is the mass of the central body (usually Earth).
The semi-major axis is the distance from the center of the orbit to the furthest point of the orbit. In other words, it is half of the longest diameter of the elliptical orbit.
The mass of the central body (e.g. Earth) directly affects the orbit time of a satellite. The higher the mass of the central body, the stronger its gravitational pull, resulting in a shorter orbit time for the satellite.
Yes, the orbit time of a satellite can be changed by altering its velocity or distance from the central body. This can be achieved through thrusters or gravitational assist maneuvers.
Yes, there are several factors that can affect the accuracy of the calculated orbit time, such as atmospheric drag, changes in the gravitational field, and irregularities in the shape of the central body. These variables must be taken into account for a more precise calculation of orbit time.