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A satellite is in a circular orbit very ...

A satellite is in a circular orbit very close to the surface of a planet. At some point it is given an impulse along its direction of motion, causing its velocity to increase `n` times . It now goes into an elliptical orbit. The maximum possible value of `n` for this to occur is

A

2

B

`sqrt(2)`

C

`sqrt(2)+1`

D

`(1)/(sqrt(2)-1)`

Text Solution

AI Generated Solution

The correct Answer is:
To solve the problem, we need to determine the maximum value of \( n \) such that a satellite, initially in a circular orbit, can still remain in an elliptical orbit after its velocity is increased \( n \) times. ### Step-by-Step Solution: 1. **Determine the Initial Velocity of the Satellite**: The initial velocity \( V_i \) of a satellite in a circular orbit very close to the surface of a planet is given by: \[ V_i = \sqrt{\frac{GM}{R}} \] where \( G \) is the gravitational constant, \( M \) is the mass of the planet, and \( R \) is the radius of the planet. 2. **Determine the Escape Velocity**: The escape velocity \( V_e \) from the surface of the planet is given by: \[ V_e = \sqrt{\frac{2GM}{R}} \] 3. **Condition for Elliptical Orbit**: For the satellite to remain in an elliptical orbit after the velocity is increased \( n \) times, the new velocity \( V_f \) must be less than or equal to the escape velocity: \[ V_f = n V_i \leq V_e \] 4. **Substituting the Expressions for Velocities**: Substituting the expressions for \( V_i \) and \( V_e \): \[ n \sqrt{\frac{GM}{R}} \leq \sqrt{\frac{2GM}{R}} \] 5. **Simplifying the Inequality**: We can simplify this inequality by squaring both sides (since both sides are positive): \[ n^2 \frac{GM}{R} \leq \frac{2GM}{R} \] Canceling \( \frac{GM}{R} \) from both sides (assuming \( GM/R \neq 0 \)): \[ n^2 \leq 2 \] 6. **Finding the Maximum Value of \( n \)**: Taking the square root of both sides gives: \[ n \leq \sqrt{2} \] Therefore, the maximum possible value of \( n \) is: \[ n = \sqrt{2} \] ### Conclusion: The maximum possible value of \( n \) for the satellite to still remain in an elliptical orbit after the impulse is: \[ \boxed{\sqrt{2}} \]
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