![]() ![]() ![]() ![]() The engine control system, as in real life, consists of turbo-compressor (gas-generator- GG) RPM governor, power-turbine RPM governor, automatic engine start-up and acceleration devices, electronic engine governor (EEG) that limits the max EGT and monitors/limits the power-turbine RPM. Flame-out is modeled using air-fuel ratio calculation in the combustion chamber. Contacts with the ground and external objects are modeled based on rigid contact points system.Ĭompressor choking caused by intake icing is modeled so that it leads to power loss, EGT increase, compressor stall and engine flame-out. Aerodynamic forces acting on each sub-element of the airframe are calculated separately in their own coordinate system taking into account local airspeed of the sub-element. Each sub-element is calculated by independent lift-drag coefficients diagrams, damage degree influencing the lift properties, and center of gravity (CG) position and inertial characteristics. Each of these has its own position and orientation within the airframe local-coordinate system and each has their own aerodynamic characteristics. The Ka-50 airframe aerodynamic properties are derived from its sub-element parameters: fuselage, wings, tail, and landing gear. In essence, this means that all external forces and force momentums are used to calculate a body's position and rotation in 3-D space. F6 BL1 – resultant forces of blade elements T – resultant tractive force of rotors, T = ∑ 1 6∑ 1 6FiBLj Rigid body dynamics equations have been used to calculate the helicopter's flight trajectory. ![]()
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