WOLFRAM SYSTEM MODELER
LateralDerivativesCalculates lateral stability and control derivatives |
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Wolfram Language
In[1]:=
SystemModel["Aircraft.StateSpace.FixedWing.Blocks.LateralDerivatives"]
Out[1]:=
Information
This model calculates the lateral stability and control derivatives according to the method presented by Nelson [1] for the given reference flight condition and based on the parameters of the aircraft given in the complete aircraft model.
References
[1] Nelson, R. C. (1998) Flight Stability and Automatic Control. 2nd ed. McGraw-Hill.
Available at: http://home.eng.iastate.edu/~shermanp/AERE355/lectures/Flight_Stability_and_Automatic_Control_N.pdf.
Parameters (20)
| mAC |
Value: Type: Mass (kg) Description: Aircraft mass |
|---|---|
| IxxDry |
Value: Type: MomentOfInertia (kg⋅m²) Description: Aircraft moment of inertia about x-axis (with total mass for electric aircraft and gliders) |
| IzzDry |
Value: Type: MomentOfInertia (kg⋅m²) Description: Aircraft moment of inertia about z-axis (with total mass for electric aircraft and gliders) |
| bWing |
Value: Type: Length (m) Description: Main wing span |
| SrefWing |
Value: Type: Area (m²) Description: Main wing reference area |
| lambdaWing |
Value: Type: Angle (rad) Description: Main wing sweep angle at 1/4 chord |
| ARwing |
Value: Type: Real Description: Main wing aspect ratio |
| kCnDeltaAil |
Value: Type: Real Description: Empirical factor for the yaw moment derivative due to ailerons. Based on Figure 3.12 in Flight Stability and Automatic Control 2nd Edition |
| lVTcm |
Value: Type: Length (m) Description: Vertical tail arm length (from aircraft center of mass to vertical tail 1/4 chord) |
| zVTacCM |
Value: Type: Length (m) Description: z-coordinate w.r.t. aircraft center of mass of center of pressure of vertical tail |
| CyDeltaRdr |
Value: Type: Real (rad⁻¹) Description: Y-force due to rudder deflection control derivative |
| ClDeltaAil |
Value: Type: Real (rad⁻¹) Description: Roll moment due to aileron deflection control derivative |
| Cldeltar |
Value: Type: Real (rad⁻¹) Description: C_l_delta_r (Coefficient for change in roll moment due to rudder deflection) |
| Cndeltar |
Value: Type: Real (rad⁻¹) Description: C_n_delta_r (Coefficient for change in yaw moment due to rudder deflection) |
| CyBeta |
Value: Type: Real (rad⁻¹) Description: Y-force due to sideslip angle stability derivative |
| ClRoll |
Value: Type: Real (rad⁻¹) Description: C_l_p (Coefficient for change in roll moment due to roll rate) |
| Cnr |
Value: Type: Real Description: C_n_r (Coefficient for change in yaw moment due to yaw rate) |
| Cyr |
Value: Type: Real (rad⁻¹) Description: C_y_r (Coefficient for change in Y-force due to yaw rate) |
| Cnbeta |
Value: Type: Real (rad⁻¹) Description: C_n_beta (Coefficient for change in yaw moment due to sideslip angle) |
| Clbeta |
Value: Type: Real (rad⁻¹) Description: C_l_beta (Coefficient for change in roll moment due to sideslip angle) |
Connectors (2)
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lateraldervsOut |
Type: RealVectorOutput[14] Description: Lateral derivatives output |
|---|---|---|
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subLateralDervsBus |
Type: RefFlightSignalBus Description: Bus port for reference flight conditions input |
Used in Components (1)
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Aircraft.StateSpace.FixedWing Aircraft model using state-space representation |