Take a look at the following new Aviator features in STK 11.6 and prepare to be wowed!
The calculation is modified to compute the pitch rate at zero flight path angle and that pitch rate is then converted to the required acceleration at the actual flight condition. The need for this feature is typically encountered when a user specifies a push over load factor close to 1.0 G to model gentle non-aggressive maneuvers.
When the flight path angle is high, the steady state load factor to hold that flight path angle could be less than the specified push over load factor, making it impossible to push over and reduce the flight path angle.
- The new Aero/Prop maneuver mode enables a more realistic application of the performance capabilities without affecting any existing use cases, specifically for turns and push/pull maneuvers. It captures how aircraft can maneuver more aggressively at higher speeds simply due to the lift-generation capability. It also enables Basic Maneuver procedures to match the available vertical plane capability to the required horizontal plane maneuver, so the aircraft flies a more realistic trajectory.
- The ability to ignore the flight path angle when computing the vertical plane accelerations has been added to handle the situation where maneuvering limits are specified, but the aircraft is flown in a way where those limits prevent the aircraft from being able to perform the requested maneuver.
- Optional temperature, Mach and dynamic pressure limits were added to the Missile performance model system to augment the values specified for climb/cruise/descent performance model speeds.
- A new wizard has been added to allow for the easy computation of the appropriate fuel flow for the Reference State procedure.
- The contour display on the Advanced Fixed Wing External Powerplant UI now handles non-linear data more appropriately.
- Q (dynamic pressure) and TASDot were added as inputs to the various MATLAB control and guidance strategies. This enables the ability to more easily model the effects of aerodynamics, and incorporate the longitudinal acceleration of the vehicle into its control and guidance processing when Aviator is handling the TASDot calculations.
Everything is modeled in Aviator