Development of mathematical models of the flight dynamics of rotary-wing aircraft


Аuthors

Adayeva S. Y.1, Borisov A. E.2*, Maxim Y. K.1, Vladimir S. K.1, Rubinshteyn M. A.2*

1. Central Aerohydrodynamic Institute named after N.E. Zhukovsky (TsAGI), Zhukovsky, Moscow region, Russia
2. Central Aerohydrodynamic Institute named after N.E. Zhukovsky (TsAGI), 1, Zhukovsky str., Zhukovsky, Moscow Region, 140180, Russia

*e-mail: spintest@tsagi.ru

Abstract

The next step of the development of TsAGI’s mathematical models of flight dynamics of rotary-wing aircraft is presented. A universal mathematical model of the motion of a "generalized" rotary-wing aircraft has been updated by dynamics models of multirotor lift-propulsion system and tilted tail-rotor. Thus there are six generalized rotorcraft configurations can be modeled: single-rotor with tail rotor, coaxial-rotors, tandem-rotors, transverse-rotors, tilted-rotor, multirotor lift-propulsion systems.
Three main groups of flight dynamic problems of rotary-wing aircraft are considered to be solved by model of corresponding level of complexity. The 1st level includes stability problems and initial development of algorithms of flight control systems. The 2nd level includes numerical studies of steady and transitional modes of flight with active flight control system, experimental research of maneuverability and controllability on flight simulation devices with a man in control circuit, verification of rotary-wing design solutions and expertise of flight safety depending on technical issues, getting 1st level linear models of dynamic. The 3rd level includes assessment of structural loads in parts of rotary-wing system, research of aero-elasticity phenomena and limiting flight modes. The 3rd level models underlies the 2nd level ones, the 2nd level models underlies 1st level ones.  
The brief overview of key features of techniques applied on every level is given. Among peculiarities of model is the algorithm of induced velocities calculation in case of multirotor system. Rotary-wing aircraft exploratory research techniques are supplemented by specially developed software to cope with large amount of input data. The model has been validated by comparison of calculated balancing characteristics and perturbed motion of single-rotor and coaxial-rotor helicopters with corresponding flight tests’ data.

Keywords:

mathematical model, flight dynamics, rotary-wing aircraft, main rotor, multirotor lift-propulsion system

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