Consider a spacecraft with moment of inertia matrix (in terms of body axis) given by: 5000 0.0 0.0 0.0 10000 0.0 kg.m? 0.0 13000 The spacecraft is performing a maneuver to get it in line-of-sight of its mission objective. The maneuver is an attitude change where the components of angular velocity in the body axis syste remain constant. The angular velocity (in rad/s) is given by: = 0.11i+0.28j+0k . What mor (N m) needs to anplied in the body z-direction durine the maneuver

Consider a spacecraft with moment of inertia matrix (in terms of body axis) given by: 5000 0.0 0.0 0.0 10000 0.0 kg.m? 0.0 13000 The spacecraft is performing a maneuver to get it in line-of-sight of its mission objective. The maneuver is an attitude change where the components of angular velocity in the body axis syste remain constant. The angular velocity (in rad/s) is given by: = 0.11i+0.28j+0k . What mor (N m) needs to anplied in the body z-direction durine the maneuver