6. For the Lockheed F-104 Starfighter, the data were obtained from Teper (1969) and describes a sea level flight condition. The dimensional aerodynamic stability and control derivatives were substituted in the longitudinal linearized equations. After taking Laplace transform and simplifying, the following resulted: [746s + 26.26 159.64 [u(s)] w(s) 36.4 + 1014 65000s² + 18135s] [0(s). -79.82 24021.2 -16502 8(s) -303575] 746s + 328.24 -227530s a. Obtain the transfer function describing pitch attitude response to elevator. b. What are the natural frequencies and damping of the longitudinal modes. c. Show the pitch attitude response of the F-104 to a 1° step of elevator. Identify the modes on the graph. (You may use MATLAB for this part.)

6. For the Lockheed F-104 Starfighter, the data were obtained from Teper (1969) and describes a sea level flight condition. The dimensional aerodynamic stability and control derivatives were substituted in the longitudinal linearized equations. After taking Laplace transform and simplifying, the following resulted: [746s + 26.26 159.64 [u(s)] w(s) 36.4 + 1014 65000s² + 18135s] [0(s). -79.82 24021.2 -16502 8(s) -303575] 746s + 328.24 -227530s a. Obtain the transfer function describing pitch attitude response to elevator. b. What are the natural frequencies and damping of the longitudinal modes. c. Show the pitch attitude response of the F-104 to a 1° step of elevator. Identify the modes on the graph. (You may use MATLAB for this part.)