Question a) b) 1) 4 (Total: 15 marks) The equation for aircraft Dutch-Roll mode of motion can be approximated by the following equation: [4] = -Vo m 0 L₂N₂ + ₂N+

Izr - (14₂-12₂) (1½ – 13/₂) - mass 7394 kg Ix Iz 0 4811.80 kgm² 80900.30 kgm² Ixz0kgm² [] + The F104 Starfighter (a fighter/interceptor) has the following parameters and aerodynamic derivatives: 0 Alt P Vo Q S 18.22 m² Cyc b 6.69 m CLE 2 2.91 m CNC -0.16 0.0042 Apply the appropriate formulate to compute and verify the numerical form of the Dutch-roll equation of motion is as follow: -0.1544 -87.451 0.2018 m ¼¸Ñƒ +1⁄₂Å£_ ¹¸Ñ‹ + ¹xzLz (Ixlz-z) (lxlz – 1⁄z). Sea level 1.225 kg/m³ 87.45 m/s 4684.1 Pa 0.208 0.045 Cy CLB 0 CNB CL CNr CLE CNE -0.2025] []+[0.02964 ii) Appraise the frequency and damping ratio of the Dutch-roll mode 2.4008 -1.1292 2992 -1.17 -0.175 2.5 0.265 -0.75 0.039 Rate the flight quality level of the F104 aircraft against MIL-8785C specification. State clearly the class and the flight phase category defined for the evaluation. To improve the flight quality, a state-space feedback system using aileron only is proposed. The aim is to achieve a damping ratio of = 0.4, while keeping the same frequency. Formulate a computation procedure and calculate the gain schedule.