How would I solve for the s_\alpha or s_r vectors using components from the listed E-Frame? Space Vehicle Dynamics

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I'm taking a dynamics class where we are specifically focusing on the transport theorem. I need to first identify the position vector, and then take 2 derivatives for inertial velocity and inertial acceleration. While I understand how that works, there's one step in the solution to the problem below that I do not currently follow.

Dynamics Problem in question that contains 3 frames, a telescoping rod, and a circle of radius r. These are both rotating CCW about the origin.

The image link below is the worked solution to the problem.

Worked correct solution to the above problem statement.

While I understand the concept as a whole, there's one step that my professor didn't go into much detail about, which is the focus of this post. I shared a screenshot below focusing on the s_\alpha portion but the derivation of s_r based on the E-Frame is also confusing.

E-frame with s alpha vector relationship

Could someone help me out with a quick explainer on how to derive these vectors from components of the E-Frame?