DCS World Su-25T Fli..

[Su-25T Frogfoot]
DCS
When an airframe component is destroyed, the plane’s motion is modeled in a natural way.
The damaged component’s aerodynamics can be fully or partially removed from the
aircraft’s aerodynamic calculations.
The flight model guarantees a realistic implementation of stalls (rocking wings with
simultaneous course oscillation).
Various characteristics of aerodynamic shaking depending on the flight mode have been
introduced. This occurs due to store loading, exceeding allowable angle of attack, Mach
number, etc.
The jet engines are represented as a complex model of the main components: compressor,
combustion chamber, turbine and starter-generator.
Idle RPM depends on the speed mode: altitude and Mach number, weather conditions:
pressure and temperature.
Low RPM over-speeding is modeled.
Engine throttling and its controllability depend on rotation speed.
Gas temperature behind the turbine is dependent on engine operating mode, flight mode
and weather condition.
Specific fuel consumption is non-linearly dependent on engine operating mode and flight
mode.
The dynamics of engine operating parameters (gas speed and temperature) during engine
start and shutdown is accurately modeled. The mode of engine autorotation from ram
airflow, engine seize (accompanied by continued temperature rise) in case of engine start
at the incorrect throttle position, engine restart and windmill air restart.
The left and right hydraulic system model includes models of sources and consumers of hydraulic
pressure.
Each hydraulic system supplies its own group of hydraulic pressure users (landing gear,
aileron actuator, flaps, wing leading edge flaps, adjustable stabilizer, nose wheel steering,
brake system, etc).
Pressure in the left and right hydraulic systems depends on the balance of hydraulic pump
efficiency and operating fluid consumption by hydraulic pressure users (boosters,
actuators, etc). Hydraulic pumps efficiency depends on the right and left engines' speed
respectively, operating fluid consumption depends on their work intensity.
Both catastrophic and partial hydraulic actuators failure when pressure drops in a
corresponding hydraulic system is modeled.
The control system includes models of the primary components: trimming mechanism and trimming
effect, hydraulic boosters in roll channel, and yaw dampener.
Pitch trimming, the yawing model and the aileron trimming mechanism model are all based
on different logics. In particular, the pitch trimming position does not influence rate
controller position at near-zero flight speed. Trimming tab serviceability depends on
electrical power in the aircraft electrical system.
Eagle Dynamics 45