To resolve this problem, understanding the relationship between a satellite's orbital period and its orbital radius is essential. Kepler's Third Law of Planetary Motion posits that the square of a satellite's orbital period (\( T \)) is directly proportional to the cube of its semi-major axis (which equates to the radius \( R \) for a circular orbit):
\(T^2 \propto R^3\)
This relationship can be expressed for an orbiting satellite as:
\(T^2 = kR^3\)
where \( k \) represents a constant of proportionality, contingent upon the gravitational constant and the Earth's mass.
Let \( T_1 \) be the time period of the first satellite and \( R \) be its orbital radius. Therefore:
\(T_1^2 = kR^3\)
For a second satellite with an orbital radius of \( 1.03R \), its time period \( T_2 \) is determined by:
\(T_2^2 = k(1.03R)^3\)
The ratio of the squares of the two time periods is:
\(\left(\frac{T_2}{T_1}\right)^2 = \frac{k(1.03R)^3}{kR^3}\)
Simplification yields:
\(\left(\frac{T_2}{T_1}\right)^2 = (1.03)^3\)
The calculation of \((1.03)^3\) is:
\(1.03^3 = 1.03 \times 1.03 \times 1.03 \approx 1.092727\\)
Consequently:
\(\left(\frac{T_2}{T_1}\right)^2 = 1.092727\)
Taking the square root of both sides provides:
\(\frac{T_2}{T_1} = \sqrt{1.092727} \approx 1.045\)
This indicates that \( T_2 \) is approximately 1.045 times the period of the first satellite, signifying a 4.5% increase.
Therefore, the time period of revolution for the second satellite is approximately 4.5% greater than that of the first. The correct answer is:
4.5%
