The Smooth Accel strategy is a 3D strategy, operating in the wind frame, that mimics the behavior of normal aircraft controls.
Roll / Pull
Select the direction that the aircraft will Roll. The Roll Rate can be derived from the current Acceleration performance model or you can override the model and enter a manual value. The Roll Rate Dot property can be used to define the rate of change of the roll rate. Select the Control Roll Angle check box to define a goal value for the aircraft's roll angle during the maneuver.
The Load Factor G can be derived from the current Acceleration performance model or you can override the model and enter a manual value. The Load Factor Dot property can be used to define the rate of change of the load factor. Select Control Pitch Angle to define a goal value for the aircraft's pitch angle during the maneuver.
Airspeed
Select a method to define the aircraft's airspeed for the maneuver from the drop-down menu and define any related properties for it.
The Min Speed Limits and Max Speed Limits properties control the behavior of STK's Aviator capability if the aircraft violates the minimum or maximum airspeed during the maneuver; select Constrain if Violated to force the aircraft to obey the limit and continue the maneuver (possibly violating physical laws), Stop if Violated to stop the maneuver at the minimum or maximum airspeed, Error if Violated to make the procedure invalid, or Ignore Limits to ignore the speed limits.
Stop Conditions
By default, the maneuver will use the Basic Stopping Conditions to determine when to stop. You can select additional conditions from the drop-down menu:
- Roll AND Load Factor Rates Achieved
- Roll OR Load Factor Rates Achieved
If you have enabled controlled roll and / or pitch angles, you can select Stop when roll angle achieved and / or Stop when pitch angle achieved to stop the maneuver if the values for those properties are achieved. These stopping conditions are independent, so that if both are selected, the maneuver will stop if either one is achieved.