A 7480-kg satellite has an elliptical orbit, as in the figure. The point on the

Question

A 7480-kg satellite has an elliptical orbit, as in the figure. The point on the orbit that is farthest from the earth is called the apogee and is at the far right side of the drawing. The point on the orbit that is closest to the earth is called the perigee and is at the far left side of the drawing. Suppose that the speed of the satellite is 2800 m/s at the apogee and 8000 m/s at the perigee.

(a) Find the work done by the gravitational force when the satellite moves from the apogee to the perigee.

(b) Find the work done by the gravitational force when the satellite moves from the perigee to the apogee.

I dont even know where to start this question.

Explanation / Answer

a.

Workdone

W= K2- K1= 0.5*m*(V2^2 - V1^2)

W= 0.5×7370×(8300²- 2710²)

W=2.26*10^11 J

b.

Workdone

W= K2- K1= 0.5*m*(V2^2 - V1^2)

W= 0.5×7370×(2710²8300²)

W=-2.26*10^11 J

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