The time period of a satellite in orbit depends on the mass of the celestial body it is orbiting and the radius of the orbit.
The formula for the time period is:
$T = 2\pi \sqrt{\frac{a^3}{GM}}$
Squaring both sides:
$T^2 = \frac{4\pi^2 a^3}{GM}$
Rearranging gives:
$\frac{a^3}{M} = \text{constant}$
Since both satellites (one orbiting Earth and the other orbiting the Moon) have the same time period, we get:
$\frac{a_e^3}{M_e} = \frac{a_m^3}{M_m}$
We know that mass $M$ of a spherical body is related to density $\rho$ by:
$M = \rho \cdot \frac{4}{3} \pi R^3$
Assuming the satellites are close to the surfaces, we take $a \approx R$, so:
$\frac{M}{a^3} \approx \rho \cdot \frac{4}{3} \pi$
This implies:
$\frac{M_e}{a_e^3} = \frac{M_m}{a_m^3} \Rightarrow \rho_e = \rho_m$
Therefore, the correct option is (C): $\rho_m = \rho_e$
The work which a body needs to do, against the force of gravity, in order to bring that body into a particular space is called Gravitational potential energy. The stored is the result of the gravitational attraction of the Earth for the object. The GPE of the massive ball of a demolition machine depends on two variables - the mass of the ball and the height to which it is raised. There is a direct relation between GPE and the mass of an object. More massive objects have greater GPE. Also, there is a direct relation between GPE and the height of an object. The higher that an object is elevated, the greater the GPE. The relationship is expressed in the following manner:
PEgrav = mass x g x height
PEgrav = m x g x h
Where,
m is the mass of the object,
h is the height of the object
g is the gravitational field strength (9.8 N/kg on Earth) - sometimes referred to as the acceleration of gravity.