 Classical Mechanics

# Applying Kepler's Laws

The distance of a $m = 9.00 \times 10 ^6 \text{ kg}$ planet from the Sun is $R = 2.00 \times 10^9 \text{ km}.$ If we stopped the planet in orbit and then let it fall straight towards the Sun, approximately how long would it take for the planet to reach the Sun in seconds?

Consider both the planet and the Sun as point masses.
The mass of the Sun is $M = 2.00 \times 10^{30} \text{ kg}.$
Gravitational constant is $G = 6.67 \times 10^{-11} \text{ Nm}^2\text{/kg}^2.$

A satellite, moving in an elliptical orbit, is $520 \text{ km}$ above Earth's surface at its farthest point and $260 \text{ km}$ above at its closest point. Calculate the semimajor axis of the orbit.

The radius of Earth is $R_e = 6.37 \times 10^6 \text{ m}.$

A $5 \times 10^4 \text{ kg}$ geo-stationary satellite revolves around the earth in a circular orbit of radius $36000 \text{ km}.$ Approximately what will be the time period of a $5 \times 10^4 \text{ kg}$ satellite in an orbit of radius $12000 \text{ km}?$

A geo-stationary satellite is a satellite whose position in the sky remains the same in the view of a stationary observer on earth.

If the distance between the earth and the sun were $9.0 \%$ of its present value, the approximate number of days in a year would be _______.

A satellite is in an elliptical orbit. If the maximum orbital velocity of the satellite is $v_M = 2.60 v_m,$ where $v_m$ is the minimum orbital velocity, what is the approximate orbital eccentricity?

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