Building a control system of a small-sized aircraft in the take-off and landing areas under wind conditions


Аuthors

Tretyakov A. V.1*, Piskunova O. I.2**

1. Dubna International University for Nature, Society and Man, 141980 Moscow region, Dubna, Universitetskaya str., 19
2. Dubna State University, Dubna, Moscow region, Russia

*e-mail: treav@mail.ru
**e-mail: ifi@uni-dubna.ru

Abstract

The paper examines the stabilization contour (SC) and control systems (CS) of a small-sized aircraft (SSA) in the longitudinal plane at the take-off and landing sites under the influence of wind disturbances with an intensity characteristic of the surface layer.

The study of SC was carried out on a mathematical model based on the SSA equations of motion linearized by the method of small perturbations. The aerodynamic and mass-inertia parameters of the SSA are defined as dynamic coefficients of the linearized SC.

The investigation was conducted by the method of frequency synthesis. The D-partitioning method was used to construct the stability range of the aircraft at the stage of preliminary assessment of its flight performance. This method has been completed by calculating the stability subdomains of margins in amplitude and phase, obtained by using of the logarithmic form of the Nyquist stability criterion. The influence of the dynamic characteristics of the steering drives and the angular velocity sensors on the formation of the stability region is taken into account.

The proposed method makes it possible to estimate the stability margins in a specified range of frequency domain functioning of the investigated systems. For performing of calculations the programs have been compiled in the language of the MATLAB software environment.

The wind disturbance is made by increasing the SSA angle of attack by a value proportional to the wind effect. The wind effect near the ground is taken into account primarily due to the low values of the air flow pressures acting on the SSA in this section of the flight. Real measurements collected on the ground, in height and relief corresponding to the conditions of the SSA launch, were used as the initial data for the wind model formation. The approximation of the wind effect is performed by using the fast Fourier transform method.

In order for the calculation results to reflect the nature of wind flow variability in the area under consideration as realistically as possible the obtained approximation got complacent with the initial data using the Kalman filter.

Recommendations on the choice of gain coefficients for SC and CS parameters are given. The proposed techniques can be used to study the stability characteristics and control the SSA balancing processes at the take-off and landing sites.

Keywords:

angular stabilization system, small-sized aircraft, aircraft stabilization, wind model, stability reserves, D-partitioning method, Kalman filter, fast Fourier transform

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