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The time period of a geostationary sat...

The time period of a geostationary satellite at a height 36000 km is 24 h a spy satellite orbits vergy close to earth surface (R=6400 km ) what will be its time period ?

A

4h

B

1h

C

2h

D

1.5 h

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The correct Answer is:
To find the time period of a spy satellite orbiting very close to the Earth's surface, we can use Kepler's third law of planetary motion, which states that the square of the time period (T) of a satellite is directly proportional to the cube of the semi-major axis (r) of its orbit. ### Step-by-Step Solution: 1. **Understanding Given Data:** - Time period of geostationary satellite, \( T_1 = 24 \) hours. - Height of geostationary satellite, \( h_1 = 36000 \) km. - Radius of the Earth, \( R = 6400 \) km. - For the spy satellite, which is very close to the Earth's surface, we can assume its height \( h_2 \approx 0 \) km. 2. **Calculate the Distance from the Center of the Earth:** - For the geostationary satellite: \[ r_1 = R + h_1 = 6400 \, \text{km} + 36000 \, \text{km} = 42400 \, \text{km} \] - For the spy satellite: \[ r_2 = R + h_2 = 6400 \, \text{km} + 0 \, \text{km} = 6400 \, \text{km} \] 3. **Applying Kepler's Third Law:** According to Kepler's third law: \[ \frac{T_1^2}{T_2^2} = \frac{r_1^3}{r_2^3} \] Rearranging gives: \[ \frac{T_1}{T_2} = \sqrt{\frac{r_1^3}{r_2^3}} \] 4. **Substituting Values:** Substitute \( T_1 = 24 \) hours, \( r_1 = 42400 \) km, and \( r_2 = 6400 \) km: \[ \frac{24}{T_2} = \sqrt{\frac{(42400)^3}{(6400)^3}} \] 5. **Calculating the Ratio:** Simplifying the right side: \[ \frac{24}{T_2} = \sqrt{\left(\frac{42400}{6400}\right)^3} \] Calculate \( \frac{42400}{6400} = 6.625 \): \[ \frac{24}{T_2} = \sqrt{(6.625)^3} \] Calculate \( (6.625)^3 \approx 291.6 \): \[ \frac{24}{T_2} = \sqrt{291.6} \approx 17.05 \] 6. **Cross-Multiplying to Solve for \( T_2 \):** \[ 24 = 17.05 \cdot T_2 \] \[ T_2 = \frac{24}{17.05} \approx 1.407 \, \text{hours} \] 7. **Final Result:** The time period of the spy satellite is approximately: \[ T_2 \approx 1.407 \, \text{hours} \approx 1.5 \, \text{hours} \text{ (rounded)} \]

To find the time period of a spy satellite orbiting very close to the Earth's surface, we can use Kepler's third law of planetary motion, which states that the square of the time period (T) of a satellite is directly proportional to the cube of the semi-major axis (r) of its orbit. ### Step-by-Step Solution: 1. **Understanding Given Data:** - Time period of geostationary satellite, \( T_1 = 24 \) hours. - Height of geostationary satellite, \( h_1 = 36000 \) km. - Radius of the Earth, \( R = 6400 \) km. ...
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