The gravitational force on a satellite decreases as it moves further away from the Earth, following the inverse square law.

The gravitational force on a satellite decreases as it moves to a higher orbit due to the inverse square law of gravitation.

The gravitational force decreases with the square of the distance from the center of the Earth. If the altitude is doubled, the distance from the center of the Earth becomes R + 2h, and the force becomes weaker by a factor of four.

As a satellite moves further away from the Earth, its gravitational potential energy increases because it is moving to a higher potential.

As a satellite moves to a higher orbit, its gravitational potential energy increases due to the increase in distance from the Earth.

Atmospheric drag decreases the speed of satellites in low Earth orbit, leading to a gradual decrease in altitude.

According to Kepler's third law, increasing the altitude of a satellite increases its orbital period.

Increasing the height of a satellite decreases its orbital speed, as the gravitational force acting on it decreases.

If the orbital speed is to remain constant, increasing the mass of the satellite requires an increase in the orbital radius due to the balance of gravitational and centripetal forces.

The mass of the satellite does not affect its orbital radius; it is determined by the mass of the Earth and the orbital speed.

The orbital speed of a satellite depends on the mass of the Earth and the radius of the orbit, but not on the mass of the satellite itself. Therefore, increasing the mass of the satellite has no effect on its orbital speed.

The escape velocity from the Earth's surface is approximately 11.2 km/s.

The escape velocity from the Earth's surface is approximately 11.2 km/s.

The escape velocity from the Earth's surface is approximately 11.2 km/s.

The gravitational force acting on a satellite in orbit is given by F = GmM/(R+h)^2, where R is the radius of the Earth.

The gravitational potential energy of a satellite at height h is given by U = -GMm/(R+h), where R is the radius of the Earth.

The minimum speed required for a satellite to achieve a low Earth orbit is approximately 7.9 km/s.

The minimum speed required for a satellite in low Earth orbit is approximately 7.9 km/s.

The orbital speed v of a satellite in a circular orbit is given by v = sqrt(GM/(R+h)^2), where G is the gravitational constant, M is the mass of the Earth, R is the radius of the Earth, and h is the height of the satellite above the Earth's surface.

The orbital speed of a satellite in low Earth orbit is approximately 7.9 km/s.

The period of a satellite in a circular orbit at a height of 300 km is approximately 90 minutes.

Satellites in low Earth orbit have a much shorter orbital period compared to geostationary satellites due to their proximity to Earth.

A satellite in a stable orbit is primarily influenced by the gravitational force exerted by the Earth.

The orbital period T of a satellite is related to its height h by T ∝ h^(3/2), which indicates that the period is inversely proportional to the square root of the gravitational force acting on it.

The period T of a satellite is proportional to the square root of the orbital radius r (T ∝ √r).

The time period T of a satellite is related to the orbital radius r by T ∝ r^(3/2), according to Kepler's third law.

The period T of a satellite is proportional to the square root of the orbital radius r, as given by T = 2π√(r^3/GM).

A geosynchronous satellite typically has a circular orbit to maintain a constant position relative to the Earth's surface.

The gravitational force depends on the masses of the objects and the distance between them, but not on the speed of the satellite.

The gravitational force depends on the masses and the distance, but not on the speed of the satellite.