The formula for calculating the orbiting height of a satellite is h = (GM/R^2)^1/3 - R, where G is the gravitational constant, M is the mass of the Earth, and R is the radius of the Earth.
The factors that affect the orbiting height of a satellite include the mass of the Earth, the gravitational constant, the velocity of the satellite, and the centripetal force acting on the satellite.
The velocity of a satellite in orbit can be determined using the formula v = √(GM/R), where G is the gravitational constant, M is the mass of the Earth, and R is the distance between the satellite and the center of the Earth.
The orbiting height of a satellite is significant because it determines the satellite's speed, stability, and visibility from the ground. It also affects the satellite's ability to communicate with Earth and its coverage area.
Yes, the orbiting height of a satellite can be changed by adjusting the satellite's velocity or by using thrusters to alter its trajectory. However, these changes must be carefully calculated to avoid collisions with other satellites or debris in orbit.