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Two satellite of masses 40kg, 50kg are r...

Two satellite of masses 40kg, 50kg are revolving around earth in different circular orbits of radii `r_(1),r_(2)` such that their kinetic energies are equal. The ratio of `r_(1),r_(2)` is

A

`sqrt(5):sqrt(4)`

B

`16:25`

C

`sqrt(45):sqrt(4)`

D

`25:16`

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The correct Answer is:
To solve the problem, we need to find the ratio of the radii \( r_1 \) and \( r_2 \) of the orbits of two satellites that have equal kinetic energies. ### Step-by-Step Solution: 1. **Understand the Kinetic Energy Formula**: The kinetic energy (KE) of a satellite in orbit is given by the formula: \[ KE = \frac{G M m}{2 r} \] where \( G \) is the gravitational constant, \( M \) is the mass of the Earth, \( m \) is the mass of the satellite, and \( r \) is the radius of the orbit. 2. **Set Up the Equation for Kinetic Energies**: For the two satellites with masses \( m_1 = 40 \, \text{kg} \) and \( m_2 = 50 \, \text{kg} \), and their respective orbital radii \( r_1 \) and \( r_2 \), we can write: \[ KE_1 = \frac{G M m_1}{2 r_1} \] \[ KE_2 = \frac{G M m_2}{2 r_2} \] Since the kinetic energies are equal, we have: \[ \frac{G M m_1}{2 r_1} = \frac{G M m_2}{2 r_2} \] 3. **Cancel Common Terms**: We can cancel \( G \) and \( M \) from both sides of the equation: \[ \frac{m_1}{r_1} = \frac{m_2}{r_2} \] 4. **Substitute the Masses**: Substitute \( m_1 = 40 \, \text{kg} \) and \( m_2 = 50 \, \text{kg} \): \[ \frac{40}{r_1} = \frac{50}{r_2} \] 5. **Cross Multiply**: Cross multiplying gives us: \[ 40 r_2 = 50 r_1 \] 6. **Rearrange to Find the Ratio**: Rearranging the equation to find the ratio \( \frac{r_1}{r_2} \): \[ \frac{r_1}{r_2} = \frac{40}{50} = \frac{4}{5} \] ### Final Answer: The ratio of the radii \( r_1 \) to \( r_2 \) is: \[ \frac{r_1}{r_2} = \frac{4}{5} \]

To solve the problem, we need to find the ratio of the radii \( r_1 \) and \( r_2 \) of the orbits of two satellites that have equal kinetic energies. ### Step-by-Step Solution: 1. **Understand the Kinetic Energy Formula**: The kinetic energy (KE) of a satellite in orbit is given by the formula: \[ KE = \frac{G M m}{2 r} ...
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