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Influence of control system algorithms on the maneuvering characteristics of the aircraft

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Abstract

The paper presents the results of a study of the flight dynamics of a hypothetical maneuverable airplane, the shortcomings of the stability and controllability characteristics of which are compensated by algorithms of the system of improving stability and controllability by introducing a complex border of the permissible angle of attack depending on the flight mode. The research was based on a mathematical model of the airplane as a material point, taking into account the restrictions on altitude and flight speed, g-load, angle of attack, as well as the rate of change of g-load and roll. The purpose of the research is to establish the effect of the operation of the specified control system algorithms on the nature and area of safe execution of the "coup-type" maneuver. As a result of the research, it was found that the functioning of special algorithms of the electric remote-control system, leads to the emergence of areas of the operational range of altitudes and flight speeds, in which there is a significant and sharp deterioration of the maneuverability of the aircraft. Consequently, any "improvement" of the aircraft's flight performance using an automatic control system requires an assessment of the effect of these changes on the aircraft's maneuverability in all possible flight modes.

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Abbreviations

c xa :

Drag coefficient

c y a :

Lifting force coefficient

M :

Mach velocity

αperm :

Permissible angle of attack

zg :

Coordinates of the aircraft in the normal earth coordinate system along the z-axis

x g :

Coordinates of the aircraft in the normal earth coordinate system along the x-axis

V instr :

Instrumental velocity [m/s]

V :

Aircraft velocity

S :

Wing area

P :

Propulsion thrust

n ya norm :

Normal available overload

\(n_{y\max }^{per}\) :

Maximum permissible operating overload

n y :

Normal overload

n ya :

Normal speed overload

n xa :

Normal tangential overload

α:

Angle of attack [deg]

m :

Aircraft weight [kg]

H :

Coordinates of the aircraft in the normal earth coordinate system along the H-axis

H min :

Minimum flight altitude [m]

g :

Free fall acceleration

G :

Weight [H]

c sec :

Fuel flow rate per second [kg/sec]

αECL :

Engine control lever position [deg]

φeng :

Engine setting angle [deg]

γa :

Roll angle [deg]

γya -max :

Maximum roll angle [deg]

ρH :

Air density at altitude H [kg/m3]

θ:

Angle of slope of the path [deg]

Ψ:

Path angle [deg]

ρ:

Air density [kg/m3

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Funding

The authors received no financial support for the research, authorship, and publication of this article.

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Authors and Affiliations

  1. Moscow State Technical University of Civil Aviation, 20 Kronstadtsky Blvd, 125993, Moscow, Russia

    Mikhail Kiselev

  2. Public Joint Stock Company Scientific Production Corporation “Irkut”, Bolshaya Pionerskaya str, 115054, Moscow, Russia

    Sergey Levitsky

  3. Moscow Aviation Institute (National Research University), Volokolamskoe shosse, 4, 125993, Moscow, Russia

    Maxim Shkurin

Authors
  1. Mikhail Kiselev
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  2. Sergey Levitsky
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  3. Maxim Shkurin
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Correspondence to Maxim Shkurin.

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Kiselev, M., Levitsky, S. & Shkurin, M. Influence of control system algorithms on the maneuvering characteristics of the aircraft. AS 5, 123–130 (2022). https://doi.org/10.1007/s42401-021-00124-8

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  • DOI: https://doi.org/10.1007/s42401-021-00124-8

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