Control allocation for a multi-rotor e-vtol aircraft using blended-inverse

Download
2021-2-25
Aksoy, Emre
In this thesis, the control allocation problem in a flight control system design for a multi-rotor eVTOL (electric Vertical Takeoff and Landing) aircraft is proposed. The vehicle consists of 20 identical rotors that are used as flight control actuators. The dynamic system is a MIMO (Multi Input Multi Output) system with more inputs than outputs, i.e. there are many solutions of the control problem. The objective is to find an efficient and redundant control solution that provides sufficient flight performance, handling quality, and power consumption. Developed control system algorithms are applied to a simulation model of the conceptual aircraft consisting of advanced and nonlinear dynamic components. By using this model, simulation based flight tests are conducted and the results are presented and evaluated. Also, redundancy of the control system is considered for flight safety. Therefore, various simulator based rotor failure scenarios are tested on the aircraft and the proposed method is also evaluated from a redundancy point of view. It is shown that robust and efficient control redistribution can be achieved using the proposed solution under challenging failure conditions.

Suggestions

Control System Design of a Vertical Take-off and Landing Fixed-Wing UAV
Cakici, Ferit; Leblebicioğlu, Mehmet Kemal (2016-05-20)
In this study, design and implementation of control system of a vertical take-off and landing (VTOL) unmanned aerial vechicle (UAV) with level flight capability is considered. The platform structure includes both multirotor and fixed-wing (FW) conventional aircraft control surfaces: therefore named as VTOL-FW. The proposed method includes implementation of multirotor and airplane controllers and design of an algorithm to switch between them in achieving transitions between VTOL and FW flight modes. Thus, VT...
Flight control system design of an uncommon quadrotor aerial vehicle
Baskın, Mehmet; Leblebicioğlu, Mehmet Kemal; Department of Electrical and Electronics Engineering (2021-9-01)
In this thesis, design of a flight control system for an uncommon quadrotor aerial vehicle is discussed. This aerial vehicle consists of two counter-rotating big rotors on longitudinal axis to increase the lift capacity and flight endurance, and two counter-rotating small tilt rotors on lateral axis to stabilize the attitude. Firstly, full nonlinear dynamic model of this vehicle is obtained by using Newton-Euler formulation. Later, derived approximate linear model around hover is statically decoupled to sim...
Active Control of Smart Fin Model for Aircraft Buffeting Load Alleviation Applications
Chen, Yong; Ulker, Fatma Demet; Nalbantoglu, Volkan; Wickramasinghe, Viresh; Zimcik, David; Yaman, Yavuz (2009-11-01)
Following the program to lest a hybrid actuation system for high-agility aircraft buffeting load alleviation oil the full-scale F/A-18 vertical fin structure, an investigation has been performed to understand the aerodynamic effects of high-speed vortical flows on the dynamic characteristics of vertical fin structures. Extensive wind-tunnel tests have been conducted on a scaled model fill integrated with piezoelectric actuators and accelerometers to measure file aft-tip vibration responses under various fre...
Hovering Control of a Tilt-Wing UAV
Çakır, Hasan; Kurtuluş, Dilek Funda (2019-09-20)
In this study, the design and analysis of hovering controller of an UAV which is capable of doing vertical take-off and landing using the fixed six rotors placed on the tilt-wing and tilt-tail will be explained. The aircraft will have four rotors on the wing and two rotors on the tail. The main wing and horizontal tail will be capable of 90° tilting. Whole flight is separated into three flight modes, which are VTOL, Transition and Forward Flight, to have a robust control on aircraft. Only hover control of t...
Control system design and implementation of a tilt rotor UAV
Cevher, Levent; Tekinalp, Ozan; Department of Aerospace Engineering (2019)
In this thesis, a hybrid vertical take off and landing unmanned air vehicle platform is designed and developed. The platform uses tricopter configuration for takeoff and landing while it uses its fixed wings for forward flight. Control algorithms are developed for the VTOL aircraft. For this purpose, first nonlinear simulation code is developed in Matlab/Simulink environment. The simulation uses the wind tunnel experimental data for the propellers and aerodynamic data obtained from a package program XFLR 5 ...
Citation Formats
E. Aksoy, “Control allocation for a multi-rotor e-vtol aircraft using blended-inverse,” M.S. - Master of Science, Middle East Technical University, 2021.