Consider an aircraft in a maneuver. At an instant in time, the angular velocity of the aircraft relativeto Earth is & = 1.6b +0.862+0.38bz (in rad/s), the velocity of the center of mass of the aircraftrelative to Earth is i = 26b, +8b2+9bg (in m/s), the angular acceleration of the aircraft relative toEarth is ã = 0.22b, +0.16b +0.04b3 (in rad/s²), and the acceleration of the center of mass of theaircraft relative to Earth is ā = 4b, +1b2+8bg (in m/s?). What is the magnitude of the velocity (in m/s)at a point on the aircraft whose position vector relative to the center of mass is 7 = 561 +4bz+7b3(in m).Note b1, b2, bz are unit vectors fixed in the aircraft reference frame.

Given, Angular velocity, ω→=1.6b^1+0.8b^2+0.38b^3rad/s The radial velocity, v→=26b^1+8b^2+9b^3m/s…

Consider an aircraft in a maneuver. At an instant in time, the angular velocity of the aircraft relative to Earth is = 1.6b +0.8bz+0.38bz (in rad/s), the velocity of the center of mass of the aircraft relative to Earth is i = 26b, +8bg+9ôg (in m/s), the angular acceleration of the aircraft relative to Earth is ä = 0.22b, +0.16bz+0.04b3 (in rad/s?), and the acceleration of the center of mass of the aircraft relative to Earth is ā = 4b, +1b9+8bg (in m/s²). What is the magnitude of the velocity (in m/s) at a point on the aircraft whose position vector relative to the center of mass is ř = 56, +4b2+7b3 in m). Note b1, b2, by are unit vectors fixed in the aircraft reference frame.

Consider an aircraft in a maneuver. At an instant in time, the angular velocity of the aircraft relative to Earth is = 1.6b +0.8bz+0.38bz (in rad/s), the velocity of the center of mass of the aircraft relative to Earth is i = 26b, +8bg+9ôg (in m/s), the angular acceleration of the aircraft relative to Earth is ä = 0.22b, +0.16bz+0.04b3 (in rad/s?), and the acceleration of the center of mass of the aircraft relative to Earth is ā = 4b, +1b9+8bg (in m/s²). What is the magnitude of the velocity (in m/s) at a point on the aircraft whose position vector relative to the center of mass is ř = 56, +4b2+7b3 in m). Note b1, b2, by are unit vectors fixed in the aircraft reference frame.