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An earth satellite traveling in the elliptical orbit shown has a speed of v (v) as it passes the end of the orbit's semi-minor axis at A. The magnitude of the total acceleration of the satellite at A, which is due to the gravitational attraction, is a (a) and is directed from A to O. When the satellite is located at A, calculate the values of a = v (at) and (ddr). Procedure: 1. Compute the absolute value |al (at) of the satellite's tangential acceleration 2. Compute the radial coordinater (r) of the sattelite's position 3. Compute the time derivative (dtheta) of the satellite's angular coordinate 0 (theta) 4. Compute the second order time derivative (ddr) of the satellite's radial coordinater (r) Note: Do not enter any numerical values from the actual problem statement into your code. All required numerical values are either pre-programmed in the code template or are to be computed from these provided values. 13 800 km A 16 000 km 8000 km P