THE PROBLEM OF AUTOMATIC CONTROL AND SAFETY CONTROL OF THE PLANE LANDING UNDER THE ACTION OF STRONG WIND MICROGUSTS

  • S.S. Kananadze NRU MAI
  • Y.V. Kosykh НИУ МАИ
  • G.N. Lebedev NRU MAI
  • A.P. Moskalev NRU MAI
  • N.I. Selvesyuk FSUE "GosNIIAS"
Keywords: Landing safety control, wind microgust, traction machine, landing hazard coefficient

Abstract

The task of ensuring the safety of landing when an aircraft hits a swirling air flow is consid-ered. At the same time, the aircraft’s getting into the vortex airflow is already poorly studied even when it is descending along the glide path. In this case the tailwind or headwind first acts on the plane, and then the plane enters the «air hole», from which it is sometimes not possible to get close to the ground if additional efforts are not made. With manual control, the engine thrust is usually changed in proportion to air speed or ground speed. However, adherence to this principle is fraught with dangerous consequences due to the significant inertia of the increase in thrust. Since when it enters the «air hole» the aircraft will not be able to cope with the task of lowering along the glide path. From this we can conclude that in various flight situations it is necessary tocompletely eliminate the process of reducing thrust compared to the normal landing mode. It’s necessary to form a special law for controlling the engine thrust. The formation of this law takes into account the given differential equations of longitudinal and lateral movement during landing and the structure of the automatic traction control circuit of the engine to form the necessary flight speed during landing. A special method is proposed for controlling airspeed using the generated set of driving actions for the engine traction control machine. The difference in behavior in alter-nating wind directions is taken into account. It is proposed to use the identifier for determining the direction and strength of the tailwind (headwind) when it enters the vortex stream. And then in the tailwind the thrust is controlled by stabilizing air speed, and in the headwind the thrust value does not change. For the successful operation of the traction control machine, a special unit for the formation of various driving actions has been formed. It’s using signals to distinguish between alternative situations of entering the vortex stream from the output of the tailwind, headwind and vertical wind identifiers. An algorithm has been formed for assessing the hazard coefficient of continued landing under the action of micropores of wind. It will allow using the received alarm signal for timely termination of this landing in extreme situations. Computer modeling confirmed the effectiveness of the proposed approach.

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Published
2020-05-02
Issue
No 7 (2019)
Section
SECTION IV. CONTROL OF AEROSPACE SYSTEMS