Simulink Control Design™ - MathWorks

TuningGrid specifies the "tuning grid" (design points). This grid should match the one used for linearization but needs not mat ...

loop: Ensure good disturbance rejection at low frequency (to track acceleration demands) and past 10 rad/s (to be insensitive t ...

loop: Ensure good disturbance rejection up to 10 rad/s. The disturbance is injected at the plant input delta. Req3 = TuningGoa ...

Transients: Ensure a minimum damping ratio of 0.35 for oscillation-free transients MinDamping = 0.35; Req4 = TuningGoal.Poles( ...

% Get tuned gain surfaces TGS = getBlockParam(ST); % Plot gain surfaces clf subplot(221), viewSurf(TGS.Kp), title('Kp') subplot( ...

Validation First validate the tuned autopilot at the 45 flight conditions considered above. Plot the response to a step change i ...

the Simulink model. This evaluates each gain surface formula at the breakpoints specified in the two Prelookup blocks and writes ...

subplot(211) plot(t,Sim_alpha.Values.Data), grid title('Incidence \alpha in degrees') subplot(212) plot(t,Sim_V.Values.Data), gr ...

subplot(211) plot(t,Sim_h.Values.Data), grid title('Altitude h in meters') subplot(212) plot(t,Sim_az.Values.Data), grid title(' ...

Tracking of the flight path angle profile remains good throughout the maneuver. Note that the variations in incidence and speed ...

rmpath(fullfile(matlabroot,'examples','control','main')) % remove example data See Also setBlockParam | slTuner | tunableSurface ...

Trimming and Linearization of the HL-20 Airframe This is Part 1 of a five-part example series on design and tuning of the flight ...

This version of the model includes the equations of motion (EOM), the force and moment calculation from the aerodynamic tables, ...

trim values of the deflections da,de,dr depend on the airframe orientation relative to the wind. This orientation is characteriz ...

Operating point specification for the Model csthl20_trim. (Time-Varying Components Evaluated at time t=0) States: (1.) csthl20_t ...

(4.) csthl20_trim/beta (8) spec: none (5.) csthl20_trim/Mach (9) spec: none (6.) csthl20_trim/Ax,Ay,Az (10-12) spec: none spec: ...

Specify the airframe position (Xe,Ye,Ze) as (0,0,-Altitude). for ct=1:40 % Set (phi,theta,psi) to (0,alpha,beta) opspec(ct).St ...

States: ---------- (1.) csthl20_trim/HL20 Airframe/6DOF (Euler Angles)/Calculate DCM & Euler Angles/phi theta psi x: 0 x: -0 ...

% Linearize airframe dynamics at each trim condition G = linearize('csthl20_trim','csthl20_trim/HL20 Airframe',ops); size(G) 8x5 ...

states are the roll angle phi, the body velocities ub,vb,wb, and the angular rates p,q,r. Accordingly, use modred to obtain a 7t ...