Automatic Landing Flare Control Design by Model-Following Control and Flight Test on X-Plane Flight Simulator

Date

2016-07-20

Author

Cetin, Ender
Kutay, Ali Türker

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

362
views

0
downloads

The aim of this study is to design a landing control system and test it on X-Plane flight simulator. Model-Following control and H-Infinity output feedback control methods are used to design the controller. In the flare part of the automatic landing system, it is desired to reduce the rate of descent in order to make aircraft touch down softly. This is accomplished by exponential decay trajectory. The trajectory which is drawn by the referenced model is followed by the linearized aircraft model. The error between commanded altitude and the current altitude converges to zero before touch down. Controller gains used in the model-following control design are calculated by using the H-Infinity output feedback control method since not all the state variables will be available for feedback in actual flight. Aircraft control commands for the flare control design in Matlab-Simulink environment are sent to the aircraft model in X-Plane flight simulator via User Datagram Protocol (UDP) and then the measured aircraft output variables are received simultaneously. The results provided in this study show that the aircraft in X-Plane flight simulator which has a nonlinear environment can be controlled by the model-following controller to satisfy the landing flare requirements. Robustness of the controller will also be evaluated against modeling errors and external disturbances.

Subject Keywords

Model-following control, Landing flare, H-infinity output feedback control, X-plane flight simulator

URI

https://hdl.handle.net/11511/52975

Conference Name

7th International Conference on Mechanical and Aerospace Engineering (ICMAE)

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

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...
Optimal input design and system identification for an agile aircraft Millidere, Murat; Akgül, Ferhat; Leblebicioğlu, Mehmet Kemal; Department of Engineering Sciences (2021-9) This doctorate study aims to provide a methodology for developing aerodynamic and engine thrust models using simulated flight test data for the F16 fighter aircraft. An accurate and comprehensive representation of an aircraft's aerodynamic characteristics is required to design a flight control system or develop a high-fidelity flight simulator. Modern computational methods and wind tunnel testing can provide the aerodynamic database, but flight test data is required to obtain a more accurate and realistic a...
Simulator based evaluation of adaptive envelope protection algorithms for active sidestick controllers Ünal, Zeynep; Yavrucuk, İlkay; Department of Aerospace Engineering (2019) In this thesis, a simulator environment with an active control system is developed for testing different force feedback maps for flight envelope limit avoidance. Previously developed flight envelope protection algorithm; named direct adaptive limit margin estimation method is improved with Single Hidden Layer Neural Network. Neural network based adaptive models are developed online using concurrent learning algorithm for weight update laws. Concurrent learning method uses both current data and recorded past...
Structured H-Infinity controller design and analysis for highly maneuverable jet aircraft Özkan, Salih Volkan; Tekinalp, Ozan; Department of Aerospace Engineering (2022-2-10) Robust control technique is utilized to develop flight control laws for highly maneuverable aircraft. A structured H-Infinity controller is used to optimize the gains of the proposed control algorithm. For this purpose systune algorithm available in Matlab is employed to successfully obtain the controller gains satisfying selected design requirements. Designed control laws are evaluated according to these requirements and validation of the methodology is presented.

Citation Formats

E. Cetin and A. T. Kutay, “Automatic Landing Flare Control Design by Model-Following Control and Flight Test on X-Plane Flight Simulator,” presented at the 7th International Conference on Mechanical and Aerospace Engineering (ICMAE), London, ENGLAND, 2016, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/52975.