Advanced Acceleration

The Advanced Acceleration performance model is comprised of a set of parameters that define the flight characteristics of the aircraft when accelerating and is mapped to the physical properties of the aircraft that are currently defined in the Advanced Fixed Wing Tool.

Parameters

There are four parameter groups for the Advanced Acceleration performance model apart from the properties that it derives from the Advanced Fixed Wing Tool - Level Turns, Climb and Descent Transitions, Attitude Transitions, and Acceleration.

Level Turns

The values specified for these parameters are the level turn values for the aircraft. Aviator will adhere to these values when possible, but in procedures where the turn is non-level the values may be adjusted to maintain the correct relationship between these interrelated parameters. Select one parameter to manually define; the other parameters will be calculated relative to the parameter that you have specified.

Table - Level Turns ParametersClosed

Field Description
Turn G The standard G force of the aircraft in a turn.
Bank Angle The standard bank angle of the aircraft in a turn.
Turn Acceleration The standard acceleration of the aircraft in a turn.
Turn Radius A fixed turn radius that is independent of the aircraft's speed.
Turn Rate The standard turn rate.
Scale by atmospheric density Select to consider dynamic pressure when calculating turn radius; the aircraft will perform with lower G force at high altitudes because of reduced lift.

Climb and Descent Transitions

The values specified for these parameters define the G force of transitions between climbing or descending and level flight.

Table - Climb and Descent Transitions ParametersClosed

Parameter Description
Pull Up G Defines the force normal to the velocity vector used to transition into a climb or to transition out of a dive into the next flight segment. The minimum value is 1.05 G. Low values increase the likelihood of terrain impact when a procedure is defined with a high rate of descent close to the ground.
Push Over G Defines the force normal to the velocity vector used to transition into a descent or to transition from a climb to the next flight segment. The maximum value is 0.95 G. High values increase the likelihood of exceeding the ceiling when a procedure is defined with a high climb rate at an altitude close to the ceiling.
Scale by atmospheric density Select to consider dynamic pressure when calculating G force; the aircraft will perform with lower G force at high altitudes because of reduced lift.

Attitude Transitions

Aircraft attitude is determined using a 123 Euler angle sequence of Bank, Angle of Attack, and Sideslip, originating from a velocity aligned, nadir constrained set of axes. Attitude rates may be violated in the case of very short - or zero distance - procedures.

Table - Attitude Transitions ParametersClosed

Parameter Description
Roll Rate Defines the standard roll rate - the rate at which the aircraft bank angle changes - of the aircraft in a turn. When Aviator violates the specified Turn Roll Rate, the probable cause is an unrealistic climb or descent model, or the use of climb, descent, level turn and speed change parameters that aren't well matched to the roll rate parameters of the aircraft.
AOA/Pitch Rate Defines the pitch rate when transitioning between attitude modes, between procedures, and between uncoordinated maneuvers when necessary.
Sideslip/Yaw Rate Defines the yaw rate when transitioning between attitude modes, either triggered by changes in the acceleration performance model or between takeoff/landing, normal flight, weight-on-wheels, or hover mode.

Acceleration

Field Description
Mode

Select an acceleration mode:

  • Max Accel - the rate of acceleration or deceleration will be the maximum possible for the aircraft.
  • Override G - specify below - the rate of acceleration or deceleration will be specified.
Accel G If you have selected the Override G mode, specify the rate of acceleration and deceleration in Gs.

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