ctrl Element

Main element containing the setting for the PID controllers imitating the pilot inputs during the take-off run.

Namespace: Empty

Schema: Empty

Type
Parents
Children
NameOccurrencesDescription
Sequence Sequence
      Element pElev[0, 1]

Proportional action coefficient for the flight path angle controller.

      Element pNg[0, 1]

Proportional action coefficient for nose gear steering controller.

      Element pQ[0, 1]

Proportional action coefficient for the pitch rate controller.

      Element pRud[0, 1]

Proportional action coefficient for rudder controller.

      Element pThrust[0, 1]

Proportional action coefficient for the ve-locity hold controller.

      Element iElev[0, 1]

Integral action coefficient for flight path angle controller.

      Element iNg[0, 1]

Integral action coefficient for nose gear steering controller.

      Element iQ[0, 1]

Integral action coefficient for the pitch rate controller.

      Element iRud[0, 1]

Integral action coefficient for rudder con-troller.

      Element iThrust[0, 1]

Integral action coefficient for the velocity hold controller.

      Element dElev[0, 1]

Derivative action coefficient for the flight path angle controller.

      Element dNg[0, 1]

Derivative action coefficient for nose gear steering controller.

      Element dRud[0, 1]

Derivative action coefficient for rudder con-troller.

      Element dThrust[0, 1]

Derivative action coefficient for the veloci-ty hold controller.

      Element dQ[0, 1]

Derivative action coefficient for the pitch rate controller.

      Element theta1[0, 1]

Initial reference for pitch angle after rota-tion. [deg]

      Element theta2[0, 1]

Pitch angle reference 5 seconds after main landing gear liftoff. [deg]

      Element engRateLimit[0, 1]

Rate limit for the engine thrust command. [1/s]

Attributes
NameTypeRequiredDescription
Attribute externalDataDirectorySimple Type string
Attribute externalDataNodePathSimple Type string
Attribute externalFileNameSimple Type string
See Also