Gravitational potential energy U = mgh = 10 kg * 9.8 m/s² * 5 m = 490 J, approximately 500 J.

U = mgh = 10 * 9.8 * 5 = 490 J

Gravitational potential energy U = mgh = 10 * 9.8 * 5 = 490 J.

PE = mgh = 2 * 9.8 * 10 = 196 J

Gravitational potential energy (U) = mgh = 2 kg * 9.8 m/s^2 * 10 m = 196 J.

Gravitational potential energy (U) = mgh = 2 kg * 9.8 m/s² * 10 m = 196 J.

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 gravitational potential energy is given by the formula U = mgh.

The gravitational potential energy is given by U = -G * (m1 * m2) / r.

The gravitational potential energy is given by U = -G * (m1 * m2) / r.

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.

Gravitational field strength is the negative gradient of gravitational potential.

The gravitational field strength g is the negative gradient of the gravitational potential V, given by g = -dV/dr.

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).

The equipotential surfaces around a point mass are spherical.

The gravitational field lines around a point mass are radial, pointing towards the mass.

The unit of gravitational potential is Joules per kilogram (J/kg).

The standard value of gravitational acceleration at the Earth's surface is approximately 9.81 m/s².

At height R, g' = g / (2^2) = g / 4.

The standard value of gravitational acceleration at the surface of the Earth is approximately 9.81 m/s^2.

The gravitational constant G is approximately 6.67 x 10^-11 N(m/kg)^2.