A satellite follows a circular geostationary orbit, where its position can be described as x(t)=(Rsin(kt))i+(Rcos(kt))j𝑥(𝑡)=(𝑅𝑠𝑖𝑛(𝑘𝑡))i+(𝑅𝑐𝑜𝑠(𝑘𝑡))j, where R=40,000𝑅=40,000 is the radius of the orbital path in kilometres, t𝑡 is measured in hours, and k=π/12𝑘=𝜋/12.

The given equation describes the position of a satellite in a circular geostationary orbit. The position is given in terms of a coordinate system (x(t)) where 'i' and 'j' are the unit vectors along the x and y axis respectively.

The satellite's position is described by two components:

1. The x-component: x(t) = Rsin(kt)i
2. The y-component: y(t) = Rcos(kt)j

Here, R is the radius of the orbital path, which is given as 40,000 km. 't' is the time, measured in hours, and 'k' is a constant, given as π/12.

The sin and cos functions describe the circular motion of the satellite, with the sin function representing the motion along the x-axis and the cos function representing the motion along the y-axis. The variable 't' inside these functions indicates that the position changes with time, as we would expect for a satellite in orbit.

The constant 'k' determines the speed of the satellite. The smaller the value of 'k', the slower the satellite moves, and vice versa. In this case, k=π/12, which means the satellite completes a full orbit every 24 hours (since there are 2π radians in a full circle and 24 hours in a day). This is consistent with the definition of a geostationary orbit, where the satellite completes one full orbit every 24 hours.