How do you calculate the period of a satellite in circular orbit?

To calculate the period of a satellite in circular orbit, use the formula T = 2π√(r³/GM).

The period of a satellite in circular orbit is the time it takes for the satellite to complete one full orbit around the planet. This can be calculated using the formula T = 2π√(r³/GM), where T is the period in seconds, r is the radius of the orbit in meters, G is the gravitational constant (6.67 x 10^-11 Nm^2/kg^2), and M is the mass of the planet in kilograms.

To use this formula, first determine the radius of the orbit and the mass of the planet. The radius can be given in the problem or can be calculated using the altitude of the satellite and the radius of the planet. The mass of the planet can also be given in the problem or can be looked up.

Once you have the radius and mass, plug them into the formula and solve for T. Make sure to use the correct units for each variable. The answer will be in seconds.

It is important to note that this formula only works for circular orbits. If the orbit is elliptical, a different formula must be used. Additionally, this formula assumes that the satellite is in a vacuum and there are no other forces acting on it. In reality, there may be atmospheric drag or other forces that affect the period of the satellite.

A-Level Physics Tutor Summary: To find out how long a satellite takes to orbit a planet in a circular path, use the formula T = 2π√(r³/GM). This needs the orbit's radius (r), the gravitational constant (G = 6.67 x 10^-11 Nm²/kg²), and the planet's mass (M). Remember, this only applies to circular orbits and assumes no other forces like air resistance affect the satellite.