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nonlinearDynamics

Class: Aero.FixedWing
Namespace: Aero

Calculate dynamics of fixed-wing aircraft

Since R2021a

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Syntax

state_derivatives = nonlinearDynamics(aircraft,state)

Description

state_derivatives = nonlinearDynamics(aircraft,state) returns the column vector of state_derivatives of the fixed-wing aircraft aircraft from the initial state state.

Input Arguments

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Aero.FixedWing object, specified as a scalar.

Aero.FixedWing.State specified as a scalar.

Output Arguments

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State derivatives with respect to time, returned as a vector. The rate vector size depends on the degrees of freedom, and is defined in the following form:

4th order point mass:
  DYDT(1) = dXN/dt
  DYDT(2) = dXD/dt
  DYDT(3) = dU/dt
  DYDT(4) = dW/dt
 
6th order point mass:
  DYDT(1) = dXN/dt
  DYDT(2) = dXE/dt
  DYDT(3) = dXD/dt
  DYDT(4) = dU/dt
  DYDT(5) = dV/dt
  DYDT(6) = dW/dt
 
3 DOF:
  DYDT(1) = dXN/dt
  DYDT(2) = dXD/dt
  DYDT(3) = dU/dt
  DYDT(4) = dW/dt
  DYDT(5) = dQ/dt
  DYDT(6) = dTheta/dt
 
6 DOF:
  DYDT(1) = dXN/dt
  DYDT(2) = dXE/dt
  DYDT(3) = dXD/dt
  DYDT(4) = dU/dt
  DYDT(5) = dV/dt
  DYDT(6) = dW/dt
  DYDT(7) = dP/dt
  DYDT(8) = dQ/dt
  DYDT(9) = dR/dt
  DYDT(10) = dPhi/dt
  DYDT(11) = dTheta/dt
  DYDT(12) = dPsi/dt

Examples

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Open Live Script

This example shows how tp calculate the dynamics of Cessna 182.

[C182, CruiseState] = astC182();
dydt = nonlinearDynamics(C182, CruiseState)
dydt = 12×1
103 ×

    0.2201
         0
    0.0016
   -2.2163
         0
    0.0003
         0
    0.0014
         0
         0
      ⋮

Limitations

When used with Simulink.LookupTable objects, this method requires a Simulink® license.

Version History

Introduced in R2021a

See Also

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