WOLFRAM SYSTEM MODELER
This model compiles the linearized state space representation of the longitudinal motion (in body frame) of an aircraft. The linearization is done over the reference flight conditions that are inputs from the subRefFlightSignalBus connector, and the states, inputs and outputs are perturbations from the reference flight conditions.
Other inputs to this model are the perturbations to the control actuators: DeltaeIn (Δδe) for elevator deflection perturbation and DdeltaTIn (ΔδT) for throttle position perturbation. Additionally, the longitudinal stability and control derivatives are inputs through the longdervsIn connector. The output from this model is the output vector yvec through the subLongMotSignalBus bus port.
The state space representation of the longitudinal motion is in the following form
where x is the state vector and η is the control vector consisting of different perturbation components that are described in Table 1. The matrices A and B contain the stability and control derivatives, respectively. The output vector y consists of the three first components of x in Table 1. 
Table 1: Perturbation components of state and control vectors in state space representation of longitudinal motion.
|x||Δu axial velocity|
|Δw normal velocity|
|Δq pitch rate|
|Δθ pitch angle|
|η||Δδe elevator deflection|
|ΔδT throttle position|
 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.
Description: Number of engines
Description: Elevator deflection perturbation input
Description: Throttle perturbation input
Description: Input vector of longitudinal derivatives
Description: Bus port for output vector output
Description: Bus port for reference flight conditions input
Aircraft model using state-space representation