Table 2.1: Trainer 60 ARF measurements, experimentally determined iner tias as shown in Subsection 2. 1.1. Symbolic notation is borrowed from Ref. 27 Measurement Value Units Symbol (SI) Wing Spa 1.707 b Wing Area 0.5200 S Chord length 0.305 Wing Incidence 1 de Wing dihedral deg Wing Sweep 0.0de Tail area 0.0879m2 Tail Spa 0.606 b t Fin area 0.0324m2 Fin Span 0.216m Fin Offset X 1.143 Fin offset Z 0.120 h Fin Sy deg A Fin volume 0.0189 0.130 Fuselage Length.270 lb Gross mass 5267kg Empty Mass 4.798 ne Roll iner 0.31 kg.m2I Pitch inertia 0.46kg·m2 Yaw inertia* 0.63kg·m22 Aircraft Inertia ex periment The aircraft pitch, roll, and yaw inertias are important parameters for the accurate HWIL simulation of the aircraft dynamics. Fortunately, due to the small scale of the rcraft, experimental measurements can be easily made for each axis of the aircraft. The experimental setup for the roll axis is shown in Figure 2-2. From the aircraft free body diagram, the tension in each cable, T, is ngTable 2.1: Trainer 60 ARF measurements, experimentally determined iner￾tias as shown in Subsection 2.1.1. Symbolic notation is borrowed from Ref. [27] Measurement Value Units Symbol (SI) Wing Span Wing Area Chord Length Wing Incidence Wing Dihedral Wing Sweep Tail Area Tail Span Tail Offset X Tail Sweep Fin Area Fin Span Fin Offset X Fin Offset Z Fin Sweep Fin Volume Ratio Fuselage CX Area Fuselage Length Gross Mass Empty Mass Roll Inertia* Pitch Inertia* Yaw Inertia* 1.707 0.5200 0.305 1 5 0.0 0.0879 0.606 1.14 9 0.0324 0.216 1.143 0.120 53 0.0189 0.130 1.270 5.267 4.798 0.31 0.46 0.63 m m2 m deg deg deg m2 m m deg m2 m m m deg ­ m2 m kg kg kg m2 · kg m2 · kg m2 · b S c¯ Γ Λ Λ l b St t t t Sf bf lf Λ hf f V¯f I I I m l Sb b m e xx yy zz Aircraft Inertia Experiment The aircraft pitch, roll, and yaw inertias are important parameters for the accurate HWIL simulation of the aircraft dynamics. Fortunately, due to the small scale of the aircraft, experimental measurements can be easily made for each axis of the aircraft. The experimental setup for the roll axis is shown in Figure 2­2. From the aircraft free body diagram, the tension in each cable, T, is 2T = mg (2.1) 33