title: Ð ÐµÑÐµÐ½Ð¸Ðµ Ð¾Ð±ÑÐ°ÑÐ½Ð¾Ð¹ Ð·Ð°Ð´Ð°ÑÐ¸ Ð´Ð¸Ð½Ð°Ð¼Ð¸ÐºÐ¸ Ð¿Ð¾Ð»ÐµÑÐ° ÑÐ°Ð¼Ð¾Ð»ÐµÑÐ°
title: Ð²ÑÐ¿ÑÑÐºÐ½Ð°Ñ ÐºÐ²Ð°Ð»Ð¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¾Ð½Ð½Ð°Ñ ÑÐ°Ð±Ð¾ÑÐ° Ð±Ð°ÐºÐ°Ð»Ð°Ð²ÑÐ°
titleType: Subtitle
title: Inverse problem of aircraft flight dynamics
Creators: name: ÐÐ±ÑÐºÐ°ÑÐ¾Ð², Ð¢Ð¸Ð¼ÑÑ
Publisher: name: Ð¡Ð°Ð½ÐºÑ-ÐÐµÑÐµÑÐ±ÑÑÐ³ÑÐºÐ¸Ð¹ Ð¿Ð¾Ð»Ð¸ÑÐµÑÐ½Ð¸ÑÐµÑÐºÐ¸Ð¹ ÑÐ½Ð¸Ð²ÐµÑÑÐ¸ÑÐµÑ ÐÐµÑÑÐ° ÐÐµÐ»Ð¸ÐºÐ¾Ð³Ð¾
Year: 2022
Subjects: Ð¼Ð°ÑÐµÐ¼Ð°ÑÐ¸ÑÐµÑÐºÐ°Ñ Ð¼Ð¾Ð´ÐµÐ»Ñ
ÑÐ°Ð¼Ð¾Ð»ÐµÑ
Ð¾Ð±ÑÐ°ÑÐ½Ð°Ñ Ð·Ð°Ð´Ð°ÑÐ°
Ð°ÑÑÐ¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÐºÐ°
ÑÐ¸Ð½ÑÐµÐ·
ÑÐ¿ÑÐ°Ð²Ð»ÐµÐ½Ð¸Ðµ
mathematical model
aircraft
inverse problem
aerodynamics
synthesis
control

description: ÐÐ±ÑÐµÐºÑ Ð¸ÑÑÐ»ÐµÐ´Ð¾Ð²Ð°Ð½Ð¸Ñ: ÑÐ°Ð¼Ð¾Ð»ÐµÑ Ð¼Ð¾Ð´ÐµÐ»Ð¸ Boeing 747-100. ÐÑÐµÐ´Ð¼ÐµÑ Ð¸ÑÑÐ»ÐµÐ´Ð¾Ð²Ð°Ð½Ð¸Ñ: Ð¼Ð¾Ð´ÐµÐ»Ð¸ Ð°ÑÑÐ¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÐºÐ¸ Ð¸ Ð¼ÐµÑÐ¾Ð´Ñ ÑÐµÐ¾ÑÐ¸Ð¸ Ð°Ð²ÑÐ¾Ð¼Ð°ÑÐ¸ÑÐµÑÐºÐ¾Ð³Ð¾ ÑÐ¿ÑÐ°Ð²Ð»ÐµÐ½Ð¸Ñ. Ð¦ÐµÐ»ÑÑ Ð´Ð°Ð½Ð½Ð¾Ð¹ Ð´Ð¸Ð¿Ð»Ð¾Ð¼Ð½Ð¾Ð¹ ÑÐ°Ð±Ð¾ÑÑ ÑÐ²Ð»ÑÐµÑÑÑ Ð¸ÑÑÐ»ÐµÐ´Ð¾Ð²Ð°Ð½Ð¸Ðµ Ð¼ÐµÑÐ¾Ð´Ð¾Ð² ÑÐµÑÐµÐ½Ð¸Ñ Ð¾Ð±ÑÐ°ÑÐ½Ð¾Ð¹ Ð·Ð°Ð´Ð°ÑÐ¸ Ð´Ð¸Ð½Ð°Ð¼Ð¸ÐºÐ¸ Ð¿Ð¾Ð»ÐµÑÐ°, Ð°Ð½Ð°Ð»Ð¸ÑÐ¸ÑÐµÑÐºÐ¸Ð¹ ÑÐ¸Ð½ÑÐµÐ· ÑÐ¸ÑÑÐµÐ¼Ñ Ð°Ð²ÑÐ¾Ð¼Ð°ÑÐ¸ÑÐµÑÐºÐ¾Ð³Ð¾ ÑÐ¿ÑÐ°Ð²Ð»ÐµÐ½Ð¸Ñ, ÐµÐµ Ð¿ÑÐ¾Ð³ÑÐ°Ð¼Ð¼Ð½Ð°Ñ ÑÐµÐ°Ð»Ð¸Ð·Ð°ÑÐ¸Ñ Ð¸ Ð¿ÑÐ°ÐºÑÐ¸ÑÐµÑÐºÐ¾Ðµ ÑÐµÑÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ðµ. Ð Ð°Ð±Ð¾ÑÐ° ÑÐ¾ÑÑÐ¾Ð¸Ñ Ð¸Ð· Ð²Ð²ÐµÐ´ÐµÐ½Ð¸Ñ, ÑÐµÑÑÑÐµÑ Ð³Ð»Ð°Ð² Ð¸ Ð·Ð°ÐºÐ»ÑÑÐµÐ½Ð¸Ñ. ÐÐ¾ Ð²Ð²ÐµÐ´ÐµÐ½Ð¸Ð¸ ÑÐ°ÑÑÐ¼Ð°ÑÑÐ¸Ð²Ð°ÐµÑÑÑ Ð¾Ð±ÑÐ°Ñ ÐºÐ¾Ð½ÑÐµÐ¿ÑÐ¸Ñ Ð¾Ð±ÑÐ°ÑÐ½ÑÑ Ð·Ð°Ð´Ð°Ñ Ð´Ð¸Ð½Ð°Ð¼Ð¸ÐºÐ¸. Ð Ð¿ÐµÑÐ²Ð¾Ð¹ Ð³Ð»Ð°Ð²Ðµ Ð¿ÑÐ¸Ð²Ð¾Ð´Ð¸ÑÑÑ Ð¿Ð¾Ð»Ð½Ð°Ñ Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ°Ñ Ð½ÐµÐ»Ð¸Ð½ÐµÐ¹Ð½Ð°Ñ Ð¼Ð¾Ð´ÐµÐ»Ñ Ð´Ð²Ð¸Ð¶ÐµÐ½Ð¸Ñ ÑÐ°Ð¼Ð¾Ð»ÐµÑÐ°, Ð¾Ð¿Ð¸ÑÑÐ²Ð°ÑÑÑÑ ÑÐ°ÑÐ°ÐºÑÐµÑÐ¸ÑÑÐ¸ÐºÐ¸ ÑÐ°Ð¼Ð¾Ð»ÐµÑÐ° Ð¸ Ð¿ÑÐ¸Ð²Ð¾Ð´Ð¸ÑÑÑ Ð¿Ð¾ÑÑÐ°Ð½Ð¾Ð²ÐºÐ° Ð·Ð°Ð´Ð°ÑÐ¸ ÑÐµÐ¾ÑÐ¸Ð¸ ÑÐ¿ÑÐ°Ð²Ð»ÐµÐ½Ð¸Ñ. ÐÐ¾ Ð²ÑÐ¾ÑÐ¾Ð¹ Ð³Ð»Ð°Ð²Ðµ Ð¿ÑÐ¾Ð²Ð¾Ð´Ð¸ÑÑÑ Ð¸ÑÑÐ»ÐµÐ´Ð¾Ð²Ð°Ð½Ð¸Ðµ ÑÑÑÐµÑÑÐ²ÑÑÑÐ¸Ñ Ð»Ð¸Ð½ÐµÐ¹Ð½ÑÑ Ð¸ Ð½ÐµÐ»Ð¸Ð½ÐµÐ¹Ð½ÑÑ Ð¼ÐµÑÐ¾Ð´Ð¾Ð² ÑÐ¿ÑÐ°Ð²Ð»ÐµÐ½Ð¸Ñ Ð´Ð²Ð¸Ð¶ÐµÐ½Ð¸ÐµÐ¼ ÑÐ°Ð¼Ð¾Ð»ÐµÑÐ°. Ð ÑÑÐµÑÑÐµÐ¹ Ð³Ð»Ð°Ð²Ðµ Ð¿ÑÐ¾Ð²Ð¾Ð´Ð¸ÑÑÑ Ð°Ð½Ð°Ð»Ð¸ÑÐ¸ÑÐµÑÐºÐ¸Ð¹ ÑÐ¸Ð½ÑÐµÐ· ÑÐ¸ÑÑÐµÐ¼Ñ ÑÐ¿ÑÐ°Ð²Ð»ÐµÐ½Ð¸Ñ, Ð²ÐºÐ»ÑÑÐ°ÑÑÐ¸Ð¹ Ð² ÑÐµÐ±Ñ Ð»Ð¸Ð½ÐµÐ°ÑÐ¸Ð·Ð°ÑÐ¸Ñ Ð½ÐµÐ»Ð¸Ð½ÐµÐ¹Ð½Ð¾Ð¹ ÑÐ¸ÑÑÐµÐ¼Ñ Ð¸Ð· Ð¿ÐµÑÐ²Ð¾Ð¹ Ð³Ð»Ð°Ð²Ñ, Ð¿ÐµÑÐµÑÐ¾Ð´ Ðº Ð¼Ð¾Ð´ÐµÐ»ÑÐ¼ Ð² Ð¿ÑÐ¾ÑÑÑÐ°Ð½ÑÑÐ²Ðµ ÑÐ¾ÑÑÐ¾ÑÐ½Ð¸Ð¹ Ð¸ Ð¸ÑÑÐ»ÐµÐ´Ð¾Ð²Ð°Ð½Ð¸Ðµ Ð¼Ð¾Ð´ÐµÐ»ÐµÐ¹ Ð½Ð° ÑÑÑÐ¾Ð¹ÑÐ¸Ð²Ð¾ÑÑÑ Ð¸ ÑÐ¿ÑÐ°Ð²Ð»ÑÐµÐ¼Ð¾ÑÑÑ.Ð ÑÐµÑÐ²ÐµÑÑÐ¾Ð¹ Ð³Ð»Ð°Ð²Ðµ Ð¿ÑÐµÐ´ÑÑÐ°Ð²Ð»ÐµÐ½Ð° Ð¿ÑÐ¾Ð³ÑÐ°Ð¼Ð¼Ð½Ð°Ñ ÑÐµÐ°Ð»Ð¸Ð·Ð°ÑÐ¸Ñ Ð¿Ð¾Ð»ÑÑÐµÐ½Ð½Ð¾Ð¹ Ð² Ð¿ÑÐµÐ´ÑÐ´ÑÑÐµÐ¼ Ð³Ð»Ð°Ð²Ðµ Ð»Ð¸Ð½ÐµÐ¹Ð½Ð¾Ð¹ Ð¼Ð¾Ð´ÐµÐ»Ð¸ Ð´Ð²Ð¸Ð¶ÐµÐ½Ð¸Ñ ÑÑÐµÐ´ÑÑÐ²Ð°Ð¼Ð¸ Matlab/Simulink. Ð¢Ð°ÐºÐ¶Ðµ Ð¿ÑÐ¾Ð¸ÑÑÐ¾Ð´Ð¸Ñ Ð¾ÑÐµÐ½ÐºÐ° Ð¿Ð¾Ð»ÑÑÐµÐ½Ð½ÑÑ ÑÐµÐ·ÑÐ»ÑÑÐ°ÑÐ¾Ð², Ð¿ÑÑÐµÐ¼ ÑÑÐ°Ð²Ð½ÐµÐ½Ð¸Ñ Ñ ÑÐµÐ°Ð»Ð¸Ð·Ð¾Ð²Ð°Ð½Ð½Ð¾Ð¹ Ð½ÐµÐ»Ð¸Ð½ÐµÐ¹Ð½Ð¾Ð¹ Ð¼Ð¾Ð´ÐµÐ»ÑÑ. ÐÐ°ÐºÐ»ÑÑÐµÐ½Ð¸Ðµ Ð²ÐºÐ»ÑÑÐ°ÐµÑ Ð¾ÑÐ½Ð¾Ð²Ð½ÑÐµ Ð²ÑÐ²Ð¾Ð´Ñ Ð¿Ð¾ ÑÐ°Ð±Ð¾ÑÐµ.
description: Research object: aircraft model Boeing 747-100. Research subject: aerodynamic models and methods of automatic control theory. The purpose of this bachelorâs thesis is to research methods for solving the inverse problem of flight dynamics, analytical synthesis of the automatic control system, its software implementation and practical testing. Thesis consists of an introduction, four sections and conclusion. In the introduction considers the general concept of inverse problems of dynamics.In the first section, a complete dynamic nonlinear model of aircraft motion is presented, the characteristics of the aircraft are described, and the problem statement of control theory is given. The second section examines the existing linear and non-linear methods of aircraft motion control. In the third section, an analytical synthesis of the control system is carried out, including the linearization of the non-linear system from the first section, the transition to models in the state space, and the research of models for stability and controllability. The fourth section presents the software implementation of the linear motion model obtained in the previous section using Matlab/Simulink. There is also an assessment of the results obtained by comparing with the implemented non-linear model. The conclusion includes the main results of the work.