computeLateralDirectionalFlyingQualities

Calculate dutch roll mode, roll mode, and spiral mode characteristics of state-space model

Syntax

computeLateralDirectionalFlyingQualities(modelToAnalyze)

lonFQOut = computeLateralDirectionalFlyingQualities(modelToAnalyze,linSys)

lonFQOut = computeLateralDirectionalFlyingQualities(modelToAnalyze,linSys,generatePlots)

[lonFQOut,varNameOut] = computeLateralDirectionalFlyingQualities(___,Name,Value)

Description

computeLateralDirectionalFlyingQualities(modelToAnalyze) calculates the lateral-directional flying qualities (dutch roll mode, roll mode, and spiral mode) characteristics using the linear system state-space model selected in the input dialog window and compares the results against the specified source document requirements.

lonFQOut = computeLateralDirectionalFlyingQualities(modelToAnalyze,linSys) calculates lateral-directional flying quality characteristics (dutch roll mode, roll mode, and spiral mode) using the linear system state-space model provided as an input to the function.

lonFQOut = computeLateralDirectionalFlyingQualities(modelToAnalyze,linSys,generatePlots) displays the pole-zero map for the linear system state-space model.

[lonFQOut,varNameOut] = computeLateralDirectionalFlyingQualities(___,Name,Value) returns the output results structure variable name, varNameOut, for the input argument combination in the previous syntax, according to the Name,Value arguments.

example

Examples

collapse all

Calculate Lateral-Directional Flying Qualities of Simulink Aircraft Model

Calculate the lateral-directional flying qualities of a Simulink^® aircraft model.

asbFlightControlAnalysis('6DOF', 'DehavillandBeaverAnalysisModel');
opSpecDefault = DehavillandBeaver6DOFOpSpec('DehavillandBeaverAnalysisModel');
opTrim = trimAirframe('DehavillandBeaverAnalysisModel', opSpecDefault);
linSys = linearizeAirframe('DehavillandBeaverAnalysisModel', opTrim);
latFlyingQual = computeLateralDirectionalFlyingQualities('DehavillandBeaverAnalysisModel', linSys)

Operating point search report:
---------------------------------

 Operating point search report for the Model DehavillandBeaverAnalysisModel.
 (Time-Varying Components Evaluated at time t=0)

Operating point specifications were successfully met.
States: 
----------
(1.) phi
      x:         0.021      dx:     -1.12e-20 (0)
(2.) theta
      x:        0.0653      dx:      3.91e-22 (0)
(3.) psi
      x:             0      dx:      -1.7e-20 (0)
(4.) p
      x:        -1e-20      dx:     -7.37e-12 (0)
(5.) q
      x:      3.52e-23      dx:      3.42e-10 (0)
(6.) r
      x:     -1.69e-20      dx:      -1.2e-11 (0)
(7.) U
      x:          67.3      dx:      1.79e-13 (0)
(8.) v
      x:        0.0927      dx:     -4.63e-11 (0)
(9.) w
      x:           4.4      dx:      2.02e-11 (0)
(10.) Xe
      x:     -3.86e-13      dx:          67.5
(11.) Ye
      x:     -1.18e-12      dx:      4.21e-12 (0)
(12.) Ze
      x:      -2.2e+03      dx:      5.97e-11 (0)
(13.) DehavillandBeaverAnalysisModel/Environment Model/Dryden Wind Turbulence Model  (Continuous (+q +r))/Filters on angular rates/Hpgw/pgw_p
      x:             0      dx:             0
      x:             0      dx:             0
(14.) DehavillandBeaverAnalysisModel/Environment Model/Dryden Wind Turbulence Model  (Continuous (+q +r))/Filters on angular rates/Hqgw/qgw_p
      x:             0      dx:             0
      x:             0      dx:             0
(15.) DehavillandBeaverAnalysisModel/Environment Model/Dryden Wind Turbulence Model  (Continuous (+q +r))/Filters on angular rates/Hrgw/rgw_p
      x:             0      dx:             0
      x:             0      dx:             0
(16.) DehavillandBeaverAnalysisModel/Environment Model/Dryden Wind Turbulence Model  (Continuous (+q +r))/Filters on velocities/Hugw(s)/ug_p
      x:             0      dx:             0
      x:             0      dx:             0
(17.) DehavillandBeaverAnalysisModel/Environment Model/Dryden Wind Turbulence Model  (Continuous (+q +r))/Filters on velocities/Hvgw(s)/vg_p1
      x:             0      dx:             0
      x:             0      dx:             0
(18.) DehavillandBeaverAnalysisModel/Environment Model/Dryden Wind Turbulence Model  (Continuous (+q +r))/Filters on velocities/Hvgw(s)/vgw_p2
      x:             0      dx:             0
      x:             0      dx:             0
(19.) DehavillandBeaverAnalysisModel/Environment Model/Dryden Wind Turbulence Model  (Continuous (+q +r))/Filters on velocities/Hwgw(s)/wg_p1
      x:     -8.13e-14      dx:             0
      x:      5.37e-15      dx:             0
(20.) DehavillandBeaverAnalysisModel/Environment Model/Dryden Wind Turbulence Model  (Continuous (+q +r))/Filters on velocities/Hwgw(s)/wg_p2
      x:             0      dx:             0
      x:             0      dx:             0

Inputs: 
----------
(1.) DehavillandBeaverAnalysisModel/AileronCmd
      u:       0.00234    [-0.524 0.524]
(2.) DehavillandBeaverAnalysisModel/ElevatorCmd
      u:        0.0239    [-0.524 0.524]
(3.) DehavillandBeaverAnalysisModel/RudderCmd
      u:       -0.0377    [-1.05 1.05]
(4.) DehavillandBeaverAnalysisModel/ThrottleCmd
      u:         0.493    [0 1]

Outputs: 
----------
(1.) DehavillandBeaverAnalysisModel/StatesOut
      y:     -3.86e-13    [-Inf Inf]
      y:     -1.18e-12    [-Inf Inf]
      y:      -2.2e+03    [-Inf Inf]
      y:         0.021    [-Inf Inf]
      y:        0.0653    [-Inf Inf]
      y:             0    [-Inf Inf]
      y:          67.3    [-Inf Inf]
      y:        0.0927    [-Inf Inf]
      y:           4.4    [-Inf Inf]
      y:        -1e-20    [-Inf Inf]
      y:      3.52e-23    [-Inf Inf]
      y:     -1.69e-20    [-Inf Inf]


latFlyingQual = 

  struct with fields:

    DutchRollMode: [1×1 struct]
         RollMode: [1×1 struct]
       SpiralMode: [1×1 struct]

Calculate Lateral-Directional Flying Qualities of Aero.FixedWing Object

Calculate the lateral-directional flying qualities of an Aero.FixedWing object.

[aircraft, state] = astDehavillandBeaver();
linSys = linearize(aircraft, state)
latFlyingQual = computeLateralDirectionalFlyingQualities('', linSys)

linSys =
 
  A = 
                  XN          XE          XD           U           V
   XN              0           0           0      0.9896           0
   XE              0           0           0           0           1
   XD              0           0           0     -0.1439           0
   U               0           0           0    -0.01339  -0.0004123
   V               0           0           0   -0.004288    -0.02862
   W               0           0           0     -0.1996    0.001044
   P               0           0           0  -0.0006608    -0.08777
   Q               0           0           0     0.03146   -0.002583
   R               0           0           0   0.0008302    0.003697
   Phi             0           0           0           0           0
   Theta           0           0           0           0           0
   Psi             0           0           0           0           0
 
                   W           P           Q           R         Phi
   XN         0.1439           0           0           0           0
   XE              0           0           0           0       6.475
   XD         0.9896           0           0           0   3.238e-05
   U           0.287           0     -0.2437           0      0.1845
   V       -0.006164     -0.2064           0      -44.39       9.621
   W          -1.262           0       43.92           0     -0.7921
   P       -0.001175      -5.218   -0.003787       1.771      -0.569
   Q         -0.1426  -1.697e-07      -2.947     -0.2721     -0.1121
   R       0.0001093     -0.8464      0.1728     -0.5366     0.02393
   Phi             0           1           0      0.1454   4.142e-22
   Theta           0           0           1           0   -2.99e-19
   Psi             0           0           0       1.011   2.878e-21
 
               Theta         Psi
   XN         -6.476  -0.0002227
   XE              0          45
   XD         -44.53   3.238e-05
   U           -9.89    0.008391
   V         0.03322       1.388
   W           1.043      0.1316
   P         0.00533    -0.08135
   Q         -0.0687      -0.023
   R       -0.005422    0.002902
   Phi     3.053e-19           0
   Theta           0           0
   Psi     4.394e-20           0
 
  B = 
            Aileron       Flap   Elevator     Rudder  Propeller
   XN             0          0          0          0          0
   XE             0          0          0          0          0
   XD             0          0          0          0          0
   U              0     0.6608          0     0.3456      5.018
   V           -0.3          0          0       1.94          0
   W              0      -15.8     -4.068          0          0
   P         -7.019          0          0      0.491          0
   Q              0      2.163     -10.21          0          0
   R        -0.1925          0          0     -2.509          0
   Phi            0          0          0          0          0
   Theta          0          0          0          0          0
   Psi            0          0          0          0          0
 
  C = 
             XN     XE     XD      U      V      W      P      Q      R
   XN         1      0      0      0      0      0      0      0      0
   XE         0      1      0      0      0      0      0      0      0
   XD         0      0      1      0      0      0      0      0      0
   U          0      0      0      1      0      0      0      0      0
   V          0      0      0      0      1      0      0      0      0
   W          0      0      0      0      0      1      0      0      0
   P          0      0      0      0      0      0      1      0      0
   Q          0      0      0      0      0      0      0      1      0
   R          0      0      0      0      0      0      0      0      1
   Phi        0      0      0      0      0      0      0      0      0
   Theta      0      0      0      0      0      0      0      0      0
   Psi        0      0      0      0      0      0      0      0      0
 
            Phi  Theta    Psi
   XN         0      0      0
   XE         0      0      0
   XD         0      0      0
   U          0      0      0
   V          0      0      0
   W          0      0      0
   P          0      0      0
   Q          0      0      0
   R          0      0      0
   Phi        1      0      0
   Theta      0      1      0
   Psi        0      0      1
 
  D = 
            Aileron       Flap   Elevator     Rudder  Propeller
   XN             0          0          0          0          0
   XE             0          0          0          0          0
   XD             0          0          0          0          0
   U              0          0          0          0          0
   V              0          0          0          0          0
   W              0          0          0          0          0
   P              0          0          0          0          0
   Q              0          0          0          0          0
   R              0          0          0          0          0
   Phi            0          0          0          0          0
   Theta          0          0          0          0          0
   Psi            0          0          0          0          0
 
Continuous-time state-space model.


latFlyingQual = 

  struct with fields:

    DutchRollMode: [1×1 struct]
         RollMode: [1×1 struct]
       SpiralMode: [1×1 struct]

Input Arguments

collapse all

`modelToAnalyze` — Model on which to perform flight control analysis
`''` (default) | model name

Model on which to perform flight control analysis using the linear state-space model linSys. To use a state-space model directly, set the model name to an empty string, ''.

Data Types: char | string

`linSys` — State-space model object
`''` (default) | linear state-space model object name

State-space model object used to perform flight control analysis on modelToAnalyze. To create the state-space model from the input dialog menu, set linSys to an empty string, ''. To create a valid state-space model, see linearizeAirframe.

The state-space model must have these state names:

U
W
Q
theta

Data Types: char | string

`generatePlots` — Display pole-zero map
`off` | `on`

Set to on to display pole-zero map for the linear system state-space model. Otherwise, set to off.

Data Types: char | string

Name-Value Arguments

Specify optional pairs of arguments as Name1=Value1,...,NameN=ValueN, where Name is the argument name and Value is the corresponding value. Name-value arguments must appear after other arguments, but the order of the pairs does not matter.

Before R2021a, use commas to separate each name and value, and enclose Name in quotes.

Example: 'SourceDocument','MIL1797A'

`SourceDocument` — Document for flying qualities requirements verification
`MIL8785C` (default) | `MIL1797A`

Document for flying qualities requirements verification, specified as:

MIL8785C — Flying qualities of piloted airlines
MIL1797A — Flying qualities of piloted aircraft

Data Types: char | string

`Level` — Flying qualities level
`Lowest` (default) | `All` | `1` | `2` | `3`

Flying qualities level, specified as:

Lowest — Returns the verified requirements closest to level 1 for each requirement in the selected source document.
All — Returns a struct vector with all requirement levels and their verification status.
1, 2, or 3 — Returns the desired requirement level, regardless of the verification status.

Data Types: char | string

Output Arguments

collapse all

`lonFQOut` — Dutch roll, roll, and spiral lateral-directional flying qualities
structure vector

Dutch roll, roll, and spiral lateral-directional flying qualities, returned as a structure vector.

`varNameOut` — Output results structure
scalar string | `''`

If a linear system is selected through the input dialog, varNameOut returns the results structure variable name. Otherwise, varNameOut returns an empty string.

Limitations

This function requires the Simulink Control Design™ license.

Version History

Introduced in R2019a

computeLateralDirectionalFlyingQualities

Syntax

Description

Examples

Calculate Lateral-Directional Flying Qualities of Simulink Aircraft Model

Calculate Lateral-Directional Flying Qualities of Aero.FixedWing Object

Input Arguments

`modelToAnalyze` — Model on which to perform flight control analysis
`''` (default) | model name

`linSys` — State-space model object
`''` (default) | linear state-space model object name

`generatePlots` — Display pole-zero map
`off` | `on`

Name-Value Arguments

`SourceDocument` — Document for flying qualities requirements verification
`MIL8785C` (default) | `MIL1797A`

`Level` — Flying qualities level
`Lowest` (default) | `All` | `1` | `2` | `3`

Output Arguments

`lonFQOut` — Dutch roll, roll, and spiral lateral-directional flying qualities
structure vector

`varNameOut` — Output results structure
scalar string | `''`

Limitations

Version History

See Also

Topics

computeLateralDirectionalFlyingQualities

Syntax

Description

Examples

Calculate Lateral-Directional Flying Qualities of Simulink Aircraft Model

Calculate Lateral-Directional Flying Qualities of Aero.FixedWing Object

Input Arguments

modelToAnalyze — Model on which to perform flight control analysis '' (default) | model name

linSys — State-space model object '' (default) | linear state-space model object name

generatePlots — Display pole-zero map off | on

Name-Value Arguments

SourceDocument — Document for flying qualities requirements verification MIL8785C (default) | MIL1797A

Level — Flying qualities level Lowest (default) | All | 1 | 2 | 3

Output Arguments

lonFQOut — Dutch roll, roll, and spiral lateral-directional flying qualities structure vector

varNameOut — Output results structure scalar string | ''

Limitations

Version History

See Also

Topics

`modelToAnalyze` — Model on which to perform flight control analysis
`''` (default) | model name

`linSys` — State-space model object
`''` (default) | linear state-space model object name

`generatePlots` — Display pole-zero map
`off` | `on`

`SourceDocument` — Document for flying qualities requirements verification
`MIL8785C` (default) | `MIL1797A`

`Level` — Flying qualities level
`Lowest` (default) | `All` | `1` | `2` | `3`

`lonFQOut` — Dutch roll, roll, and spiral lateral-directional flying qualities
structure vector

`varNameOut` — Output results structure
scalar string | `''`