Question

5. A wind tunnel model of an aircraft pivoted at its cg is constrained to have pitching motion only. From measurements, it is found that 1 deg of elevator control input results in 100 N. m of pitch moment about its cg. When the elevator is deflected to 5 deg and held constant, it is seen that the model goes through damped oscillations and reaches a steady state value of 5 deg of pitch attitude. Further, the time period of the oscillations is found to be 3 s and the 5% settling time is found to be 2 s. The pitch dynamic model between the elevator control input u (in radians) and the pitch angle ? (in radians) of a wind tunnel model aircraft can be written as ?(s)/U(s) = A / (Iy s^2 + bs + K) where Iy is moment of inertia of the model about the pitch axis, b is the aerodynamic pitch damping constant and K is the aerodynamic pitch stiffness about the cg of the aircraft. Estimate Iy, b and K of the model aircraft from the given information.

          5. A wind tunnel model of an aircraft pivoted at its cg is constrained to have pitching motion only. From measurements, it is found that 1 deg of elevator control input results in 100 N. m of pitch moment about its cg. When the elevator is deflected to 5 deg and held constant, it is seen that the model goes through damped oscillations and reaches a steady state value of 5 deg of pitch attitude. Further, the time period of the oscillations is found to be 3 s and the 5% settling time is found to be 2 s. The pitch dynamic model between the elevator control input u (in radians) and the pitch angle ? (in radians) of a wind tunnel model aircraft can be written as ?(s)/U(s) = A / (Iy s^2 + bs + K) where Iy is moment of inertia of the model about the pitch axis, b is the aerodynamic pitch damping constant and K is the aerodynamic pitch stiffness about the cg of the aircraft. Estimate Iy, b and K of the model aircraft from the given information.

5. A wind tunnel model of an aircraft pivoted at its cg is constrained to have pitching motion only. From measurements, it is found that 1 deg of elevator control input results in 100 N. m of pitch moment about its cg. When the elevator is deflected to 5 deg and held constant, it is seen that the model goes through damped oscillations and reaches a steady state value of 5 deg of pitch attitude. Further, the time period of the oscillations is found to be 3 s and the 5% settling time is found to be 2 s. The pitch dynamic model between the elevator control input u (in radians) and the pitch angle ? (in radians) of a wind tunnel model aircraft can be written as ?(s)/U(s) = A / (Iy s^2 + bs + K) where Iy is moment of inertia of the model about the pitch axis, b is the aerodynamic pitch damping constant and K is the aerodynamic pitch stiffness about the cg of the aircraft. Estimate Iy, b and K of the model aircraft from the given information.

Added by Anthony G.

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