The Dynamic Control procedure type for Aviator extends the concepts in BasicManeuver to a full six degrees of freedom (6dof) vehicle, controlled by elevator, aileron, rudder, and throttle. The current iteration is FixedWing only.
The Dynamic Control procedure can follow either a Dynamic Control Trim Site or End Of Previous Procedure for most aviator procedures. In either case, the aircraft trims into the previous flight condition, including the speed, turn rate and flight path angle. The attitude is set to the previous flight condition and the controls are set in the trim position. If the trim is stable, the aircraft might have a small initial transit, but it will then fly the trim trajectory.
The Dynamic Control Fixed Wing Acceleration performance model must be active to use this procedure. This performance model can be used for other procedures such as Basic Maneuver. In this case, the performance model uses a trim algorithm to create the aeropropulsion data based directly on the same unit which flies the Dynamic control.
The default aerodynamic and propulsion models for fighter and transport model, respectively, an F16 and the RCAM (Research Civil Aircraft Model). Careful attention should be taken to ensure the weights and inertial matrices in the chosen aircraft either match these aircraft or that the aero and propulsion be updated for the chosen aircraft model (wing areas, propulsion, etc..).
Strategies
The available strategies for the Dynamic Control procedure are:
- Trim hold
- VXF
Trim hold
This strategy will hold the trim values (so the intial dynamic state is maintained). In addition, it can put doublets into the system at a given time.
If Use Control Limits is enabled, by default the trim treats the aircraft as a purely mathematical object and the trim (if not directly attainable) may result in controls beyond physically possible limits. If this is option is enabled, the physical constraints on the controls are enforced and the trim may drift. This also is applied to the doublet.
| Doublet Option | Decription |
|---|---|
| None | No doublet is used |
| Longitudinal, Lateral, Yaw, Thrust | The controls applied to the doublet. |
| Start time | Begining time of the doublet. |
| Length | Duration of each pulse in the doublet (total time - 2x) |
| Magnitude | The offset from trim for the doublet. This should match control ranges as determined in the Flight Control. Thrust is always zero to one. |
VXF
The Velocity, Course, Flight Path Angle controller is based on (Aircraft fault-tolerant trajectory control using Incremental Nonlinear Dynamic Inversion - ScienceDirect). This controller uses nonlinear dynamic inversion to attain these three parameters. The data is entered as a time series of points which are either interpolated or taken as step commands.
| VXF Control | Description |
|---|---|
| Linear Interpolation | If enabled, interpolates values to commands. If not enabled, interpolates values to step commands. |
| Time | A series of increasing time points. The time points are not checked against the procedure duration, but are only used when they fall in range. |
| Velocity | An ECF velocity to achieve corresponding to the time series. |
| Course | A course to achieve corresponding to the time series. |
| Flight Path | A flight path angle to achieve corresponding to the time series. |
Basic Stop Conditions
The Basic Stopping Conditions apply to either strategy you choose.
| Basic Stopping Conditions Option | Decription |
|---|---|
| Fuel State | Aircraft stops when the fuel goes below the chosen value. |
| Time of Flight | Aircraft stops when the time exceeds the chosen value. |
| Downrange | Aircraft stops when the downrange exceeds the chosen value. |