x: 0 dx: -1.44e-11 (0)
(4.) rct_airframe1/Airframe Model/Aerodynamics & Equations of Motion/ Equations of Motion (Body Axes)/q
x: -0.00972 dx: 1.15e-16 (0)
(5.) rct_airframe1/Integrator
x: 0.000708 dx: -0.00972
(6.) rct_airframe1/az Control/Integrator/Continuous/Integrator
x: 0 dx: 0.000242
Inputs:
(1.) rct_airframe1/delta trim
u: 0.000708 [-Inf Inf]
Outputs: None
Linearize the "Airframe Model" block for the computed trim condition op and plot the
gains from the fin deflection delta to az and q:
G = linearize('rct_airframe1','rct_airframe1/Airframe Model',op);
G.InputName = 'delta';
G.OutputName = {'az','q'};
bodemag(G), grid
Tuning of a Two-Loop Autopilot