13. 12 b out 03. b out b2 E T Figure 4.14: Thrust vector control. we have a feedback control system, where K is a gain constant. The principal moments of inertia are A, A, and C about the b1, b2, and b3 axes. Write Euler's equations for a non-spinning missile (w3 show the system is stable if K < 0. ==== 0) and