WOLFRAM SYSTEM MODELER
LongitudinalDerivativesCalculates longitudinal stability and control derivatives |
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Wolfram Language
In[1]:=
SystemModel["Aircraft.StateSpace.FixedWing.Blocks.LongitudinalDerivatives"]
Out[1]:=
Information
This model calculates the longitudinal 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 (14)
| mAC |
Value: Type: Mass (kg) Description: Aircraft mass |
|---|---|
| IyyDry |
Value: Type: MomentOfInertia (kg⋅m²) Description: Aircraft moment of inertia about y-axis (with total mass for electric aircraft and gliders) |
| SrefWing |
Value: Type: Area (m²) Description: Main wing reference area |
| cWingMean |
Value: Type: Length (m) Description: Main wing mean chord length |
| CLalpha |
Value: Type: Real (rad⁻¹) Description: Change in the lift coefficient due to alpha |
| CLdeltae |
Value: Type: Real (rad⁻¹) Description: C_L_delta_e (Coefficient for change in the lift coefficient of entire aircraft due to elevator deflection) |
| Cmdeltae |
Value: Type: Real (rad⁻¹) Description: C_m_delta_e (Coefficient for change in pitch moment due to elevator deflection) |
| CDalpha |
Value: Type: Real (rad⁻¹) Description: Change in C_D due to alpha (required only for state space model) |
| CDM |
Value: Type: Real Description: Change in C_D due to Mach number (required only for state space model) |
| CMM |
Value: Type: Real Description: Change in C_M due to Mach number (required only for state space model) |
| Cmq |
Value: Type: Real (rad⁻¹) Description: C_m_q (Coefficient for change in pitch moment due to pitch rate) |
| Cmalphadot |
Value: Type: Real (rad⁻¹) Description: C_m_alphadot (Coefficient for change in pitch moment due to alphadot) |
| Cmalpha |
Value: Type: Real (rad⁻¹) Description: Change in C_M due to alpha (required only for state space model) |
| zTauTotal |
Value: Type: Length (m) Description: z-coordinate of thrust line |
Connectors (2)
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longdervsOut |
Type: RealVectorOutput[14] Description: Longitudinal derivatives output |
|---|---|---|
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subLongDervsBus |
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 |