To solve this problem, we need to understand the relationship between the angular momentum of a satellite and its orbit around the Earth.
The orbital angular momentum \( L \) of a satellite revolving around the Earth is given by the formula:
L = m \cdot v \cdot r
where:
Initially, if the orbital angular momentum is \( L \) and the distance from the Earth's center to the satellite is \( r \), then:
L = m \cdot v \cdot r
Now, the distance from the Earth's center is increased by eight times its initial value, which means the new radius is \( 8r \).
The new angular momentum \( L_{\text{new}} \) will be:
L_{\text{new}} = m \cdot v_{\text{new}} \cdot (8r).
For circular orbits, the centripetal force required for keeping the satellite in orbit is provided by the gravitational force. Therefore, using the equation for circular orbits:
\frac{G \cdot M \cdot m}{r^2} = \frac{m \cdot v^2}{r}
Solving for \( v \), we get v = \sqrt{\frac{G \cdot M}{r}}.
If the distance becomes \( 8r \), the new velocity \( v_{\text{new}} \) becomes:
v_{\text{new}} = \sqrt{\frac{G \cdot M}{8r}} = \frac{1}{\sqrt{8}}v = \frac{1}{2\sqrt{2}} v.
So, the new angular momentum is:
L_{\text{new}} = m \cdot \left(\frac{1}{2\sqrt{2}}v\right) \cdot 8r = \frac{8}{2\sqrt{2}} \cdot m \cdot v \cdot r = \frac{8}{2\sqrt{2}} \cdot L = \sqrt{2} \cdot L = \frac{8}{4} L
This simplifies to:
L_{\text{new}} = 2\sqrt{2} \cdot L \approx 3 \cdot L
Therefore, the new angular momentum is approximately 3 times the initial angular momentum, which matches the option 3L.
Given below are two statements. One is labelled as Assertion (A) and the other is labelled as Reason (R).
Assertion (A): Knowing the initial position \( x_0 \) and initial momentum \( p_0 \) is enough to determine the position and momentum at any time \( t \) for a simple harmonic motion with a given angular frequency \( \omega \).
Reason (R): The amplitude and phase can be expressed in terms of \( x_0 \) and \( p_0 \).
In the light of the above statements, choose the correct answer from the options given below: