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Suppose there is a planet orbiting about...

Suppose there is a planet orbiting about the sun at a distance 9 times the present distance of the Earth. What will be the duration of the year of the planet in terms of the year on the Earth?

A

20 years

B

9 years

C

27 years

D

18 years

Text Solution

AI Generated Solution

The correct Answer is:
To find the duration of the year of a planet orbiting the Sun at a distance 9 times the present distance of the Earth, we can use Kepler's Third Law of planetary motion. Here's a step-by-step solution: ### Step 1: Understand Kepler's Third Law Kepler's Third Law states that the square of the orbital period (T) of a planet is directly proportional to the cube of the semi-major axis (r) of its orbit. Mathematically, this can be expressed as: \[ T^2 \propto r^3 \] or \[ \frac{T_1^2}{T_2^2} = \frac{r_1^3}{r_2^3} \] ### Step 2: Define the Variables Let: - \( T_1 \) = orbital period of the new planet (in years) - \( T_2 \) = orbital period of Earth = 1 year - \( r_1 \) = distance of the new planet from the Sun = 9 times the distance of Earth - \( r_2 \) = distance of Earth from the Sun ### Step 3: Set Up the Equation From the information provided: - \( r_1 = 9 \times r_2 \) Using Kepler's Third Law: \[ \frac{T_1^2}{T_2^2} = \frac{r_1^3}{r_2^3} \] Substituting the known values: \[ \frac{T_1^2}{1^2} = \frac{(9 \times r_2)^3}{r_2^3} \] ### Step 4: Simplify the Equation This simplifies to: \[ T_1^2 = \frac{9^3 \times r_2^3}{r_2^3} \] \[ T_1^2 = 9^3 \] \[ T_1^2 = 729 \] ### Step 5: Solve for \( T_1 \) Taking the square root of both sides: \[ T_1 = \sqrt{729} \] \[ T_1 = 27 \text{ years} \] ### Conclusion The duration of the year of the planet is 27 years. ---

To find the duration of the year of a planet orbiting the Sun at a distance 9 times the present distance of the Earth, we can use Kepler's Third Law of planetary motion. Here's a step-by-step solution: ### Step 1: Understand Kepler's Third Law Kepler's Third Law states that the square of the orbital period (T) of a planet is directly proportional to the cube of the semi-major axis (r) of its orbit. Mathematically, this can be expressed as: \[ T^2 \propto r^3 \] or \[ \frac{T_1^2}{T_2^2} = \frac{r_1^3}{r_2^3} \] ...
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