Abstract
A review of existing approaches to reduce the distance run and a horizontal speed landing unmanned aerial vehicle. In this paper we investigate the dynamics of movement of the unmanned aerial vehicle with a constant angle of wing sweep. Balancing control method used to commit the landing maneuver. Such a control process is carried out by displacing part of the machine, called the load platform relative to the main portion of the apparatus. For the mathematical description of the selected control principle uses dynamic equations of motion of the system of rigid body. Mathematical models of the aerodynamic force coefficients are approximated by trigonometric functions, for use in a wide range of angles of attack. The implementation of the mathematical model of the motion is carried out by means of the library SimMechanics Matlab / Simulink software. Against the background of the overall driving dynamics further discusses the use wing warping to increase the power of resistance in order to reduce the horizontal landing speed. We consider constructive solutions drive wing warping, stand design parameters influencing the driving dynamics of an unmanned aircraft as a whole. It is proposed to consider the following structure of a mathematical model consisting of two parts: a general driving dynamics system of rigid body and the internal dynamics of the drive. This approach allows you to evaluate the impact on the overall dynamics of the movement of unmanned aircraft in flight with a variable structure of the internal dynamics of the drive. In this paper we performed numerical simulations and discuss the results characterizing the operation of the drive. We study kinematic parameters of the drive: the angle of rotation, rotational speed and angular acceleration, as well as the source specified by the control law. The results suggest the feasibility of the proposed approach.
Highlights
Для совершения маневра приземления используется балансирный способ управления
In this paper we investigate the dynamics of movement of the unmanned aerial vehicle with a constant angle of wing sweep
It is proposed to consider the following structure of a mathematical model consisting of two parts: a general driving dynamics system of rigid body and the internal dynamics of the drive
Summary
Конструктивно привод гоширования представляет собой винтовую пару. Гайка винтовой пары 2 шарнирно закреплена на корневой нервюре консоли крыла. 4. Реализация математической модели движения БПЛА в Matlab/Simulink/SimMechanics. 5. Реализация математической модели привода гоширования в Matlab/Simulink/SimMechanics. 6. Для моделирования движения привода задается исходный закон управления Signal, показанный на рис. Представление математической модели в виде нескольких уровней позволяет, оценить влияние внутренних конструктивных параметров на общую динамику движения беспилотного летательного аппарата с изменяемой структурой. Реализация математической модели движения БПЛА с изменяемой в полете структурой в MATLAB/SIMULINK/SIMMECHANICS / А.С. Задачи и математические модели движения беспилотного летательного аппарата с изменяемой в полете структурой / А.С. It is proposed to consider the following structure of a mathematical model consisting of two parts: a general driving dynamics system of rigid body and the internal dynamics of the drive This approach allows you to evaluate the impact on the overall dynamics of the movement of unmanned aircraft in flight with a variable structure of the internal dynamics of the drive.
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