Meriam, Kraige & Bolton — Kinematics of Particles: Problem 2_128

2/128 An earth satellite traveling in the elliptical orbit shown has a velocity \( v = 12,149 \) mi/hr as it passes the end of the semiminor axis at \( A \). The acceleration of the satellite at \( A \) is due to gravitational attraction and is \( 32.23 [3959/8400]^2 = 7.159 \) ft/sec\(^2\) directed from \( A \) to \( O \). For position \( A \) calculate the values of \( \dot{r} \), \( \ddot{r} \), \( \dot{\theta} \), and \( \ddot{\theta} \).