DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

Design and Flight Testing of Incremental Control Laws using Angular Accelerometer Feedback on a CS-25 Aircraft

Keijzer, Twan (2018) Design and Flight Testing of Incremental Control Laws using Angular Accelerometer Feedback on a CS-25 Aircraft. Master's, Delft University of Technology.

Full text not available from this repository.


This paper discusses the design, implementation and flight testing of an incremental Backstepping (IBS) based manual flight control law with angular accelerometer (AA) feedback. The main advantages of incremental control laws is that they only require a partial model of the system and are of low complexity. Incremental control laws for aircraft rotational motion, however, need angular acceleration measurements to compute the control increments. Previously, estimates based on angular rate measurements were used for this. The newly implemented AA feedback is expected to improve the performance by decreasing the sensor delay. The manual control laws command roll rate/angle, side slip angle and vertical load factor and have been implemented on a Cessna Citation II aircraft, which is equipped with an experimental fly-by-wire system. The IBS based control law has an integrated integral control term and uses Pseudo Control Hedging to handle actuator saturations. The IBS based control law has highly satisfactory performance in flight. Test manoeuvres included standard roll and load factor commands and asymmetric thrust handling. Fault tolerance has been compared in a nonlinear simulation for the controllers with and without AA feedback in simulation. In general, the angular accelerometer feedback improved the tolerance to mismatch substantially.

Item URL in elib:https://elib.dlr.de/125860/
Document Type:Thesis (Master's)
Title:Design and Flight Testing of Incremental Control Laws using Angular Accelerometer Feedback on a CS-25 Aircraft
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Keijzer, TwanGertjan.Looye (at) dlr.deUNSPECIFIED
Date:28 September 2018
Refereed publication:No
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Number of Pages:85
Keywords:Incremental control, nonlinear control, flight control, flight test, flight control system design, angular accelerometers, adaptive control, fault tolerant control
Institution:Delft University of Technology
Department:Faculty of Aerospace Engineerging
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:fixed-wing aircraft
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Systems and Cabin (old)
Location: Oberpfaffenhofen
Institutes and Institutions:Institute of System Dynamics and Control > Aircraft System Dynamics
Deposited By: Looye, Dr. Gertjan
Deposited On:11 Jan 2019 10:25
Last Modified:12 Jul 2019 13:30

Repository Staff Only: item control page

Help & Contact
electronic library is running on EPrints 3.3.12
Copyright © 2008-2017 German Aerospace Center (DLR). All rights reserved.