ctrl Element |
Main element containing the setting for the PID controllers imitating the pilot in-puts during the landing approach.
Namespace: Empty
Schema: Empty
Name | Occurrences | Description |
---|---|---|
Sequence | ||
pElev | [0, 1] | Proportional action coefficient for the flight path angle controller. |
pNg | [0, 1] | Proportional action coefficient for nose gear steering controller. |
pQ | [0, 1] | Proportional action coefficient for the pitch rate controller. |
pRud | [0, 1] | Proportional action coefficient for rudder controller. |
pThrust | [0, 1] | Proportional action coefficient for the ve-locity hold controller. |
iElev | [0, 1] | Integral action coefficient for flight path angle controller. |
iNg | [0, 1] | Integral action coefficient for nose gear steering controller. |
iQ | [0, 1] | Integral action coefficient for the pitch rate controller. |
iRud | [0, 1] | Integral action coefficient for rudder con-troller. |
iThrust | [0, 1] | Integral action coefficient for the velocity hold controller. |
dElev | [0, 1] | Derivative action coefficient for the flight path angle controller. |
dNg | [0, 1] | Derivative action coefficient for nose gear steering controller. |
dRud | [0, 1] | Derivative action coefficient for rudder con-troller. |
dThrust | [0, 1] | Derivative action coefficient for the veloci-ty hold controller. |
dQ | [0, 1] | Derivative action coefficient for the pitch rate controller. |
theta1 | [0, 1] | Initial reference for pitch angle after rota-tion. [deg] |
theta2 | [0, 1] | Pitch angle reference 5 seconds after main landing gear liftoff. [deg] |
engRateLimit | [0, 1] | Rate limit for the engine thrust command. [1/s] |
Name | Type | Required | Description |
---|---|---|---|
externalDataDirectory | string | ||
externalDataNodePath | string | ||
externalFileName | string |