This model does not have continuous state properties. The aircraft is assumed to be rigid and, therefore, not affected by aeroelasticity. Changing mass due to fuel burn is also not considered. The engine model does not represent any throttle position delay or engine spool time, the control response is instantaneous. This is a model of the Calspan variable-stability Learjet. This is a quasi-LPV model that uses a linearized state-space form. The matrices in the model are time-varying based on a scheduling parameter\(\rho(t)\). This vector is
$$\begin{bmatrix}
\rho
\end{bmatrix}=
\begin{bmatrix}
U \\ \delta_f
\end{bmatrix}$$
Where \(U\) is the body-axis velocity, and \(\delta_f\) is the flap deflection. The general form of the model is
$$\dot{X}(t)=f(X(t),U(t))$$
$$Y(t)=h(X(t),U(t))$$
Where \(f\) and \(h\) are nonlinear functions. This model was developed in Simulink. The Aircraft has the following properties
| Property | Value |
| MTOW | 15000 lbs |
| Cruise Speed | 464 kts |
| Max Range | 1535 nm |
| Service Ceiling | 45000 ft |
| Max Climb Rate | 6050 fpm |
The Learjet-25D has an all-moving stabilator and elevator combination.
[[Time-Varying Update Equations for Learjet-25D Model]]
[[Learjet-25D Longitudinal State-Space Model]]
[[Learjet-25D Lateral-Directional State-Space Model]]
[[Learjet-25D GCAS]]
MFA Control Law – can use a stitched model
[[MFA Testing]] – used this stitched learjet model
Sources
- J. D. Carpenter, “DEPARTMENT OF THE AIR FORCE AIR UNIVERSITY”.
Backlinks
[[Auto-GCAS]]
[[Calspan]]
[[Gain Scheduling a Pitch Controller]]
[[Linear Parameter Varying System]]
MFA Control Law
[[Simulink]]