# DCS: Ka-50 Black Shark

## Helicopter Dynamics Modeling

Rigid body dynamics equations have been used to calculate the helicopter’s flight trajectory. 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.

The Ka-50 airframe aerodynamic properties are derived from its sub-element parameters: fuselage, wings, tail, and landing gear. Each of these has its own position and orientation within the airframe local-coordinate system and each has their own aerodynamic characteristics. 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. 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.

Contacts with the ground and external objects are modeled based on rigid contact points system.

X, Y, Z – axes of reference;

V – velocity vector;

F

F

F

F

F

F

F

F1

T – resultant tractive force of rotors, T =

The Ka-50 airframe aerodynamic properties are derived from its sub-element parameters: fuselage, wings, tail, and landing gear. Each of these has its own position and orientation within the airframe local-coordinate system and each has their own aerodynamic characteristics. 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. 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.

Contacts with the ground and external objects are modeled based on rigid contact points system.

### Forces and moments applied to helicopter model

V – velocity vector;

F

_{mg}– gravity;F

_{FUZ}– aerodynamic force of fuselage;F

_{RW}– aerodynamic force of right wing;F

_{LW}– aerodynamic force of left wing;F

_{RS}– aerodynamic force of right stabilizer;F

_{LS}– aerodynamic force of left stabilizer;F

_{F}– aerodynamic force of vertical stabilizer;F1

_{BL1}...F6_{BL1}– resultant forces of blade elements;T – resultant tractive force of rotors, T =