Module 10 Review Problem A satellite consisting of two solar panels with centers of mass C1 and C 2 attached to a main body with center of mass C3 is in orbit around the earth. Frame 1 (x1 ylzl) is attached to panel 1, Frame 2 (96231222) is attached to panel 2, and Frame 3 (X 3 Y3Z 3) is attached to the main body. C1 and C2 are both located a distance d from C 3 along Y3 shown. The panels may be treated as homogeneous thin rectangular plates with the dimensions and masses shown, and the main body may be treated as a homogeneous cylinder, also with dimensions and mass shown. The solar panels are oriented at an angle 3 relative to the X 3 axis. You may treat the connecting rods holding the panels in place as massless. There is also a Frame 4 that contains the unit vector {14. (a) Find the transformation matrices from: i. Frame 1 to Frame 3 ii. Frame 3 to Frame 1 iii. Frame 1 to Frame 4 iv. Frame 4 to Frame 1 v. Frame 4 to Frame 3 vi. Frame 3 to Frame 4 (b) Find the inertia matrix [1C3] for the whole satellite. Give your answer in coordinates of Frame 3. (c) During launch= the thrusters controlling the rotation of the satellite were jostled and became misaligned. Instead of rotating about the Z 3 axis, the satellite is instead rotating with angular speed 9 CCW about the 1% axis, which is tilted at an angle 4') from 23 in the Z3 Y3 plane. Calculate the total angular momentum of the satellite with respect to the xed frame. Give your answer in coordinates of Frame 3. Qua ntity Value .0. a m \"I y\\ b 23m d 4 m / \\ '5' R 2 m \\ 1 \\ / H 3 m ' m 50 kg \\ M 200 kg 1\" 9M4 Z'W" m o 4 rad/s 5 45 30\