Testing of a flight envelope protection system for fly-by-wire aerial vehicles

Download

index.pdf

Date

2019

Author

Akmenek, Bulut Efe

Metadata

Show full item record

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

Item Usage Stats

160
views

108
downloads

Aircraft should remain in their ﬂight envelope during their operation. Monitoring these limits while coping with other mission related tasks increase the pilot workload substantially. In this thesis, envelope protection methods and tactile cues are investigated for pilot workload reduction and their effectiveness compared to both conventional methods and each other. For this purpose, a simulator environment centered around an active inceptor is established such that both rotary and ﬁxed-wing conﬁgurations are possible. With the Direct Adaptive Limit Margin Estimation method envelope boundaries are estimated. Different tactile cueing methods are developed. Via the active inceptor, cueing of the estimated limits with developed methods are tested in both piloted and pilotless simulations. Pilot reviews for tested cueing methods are scaled with the NASA-TLX method and compared with each other.

Subject Keywords

Flight control., Keywords: Tactile Cue, Haptic Cues, Active Stick, Envelope Protection, Carefree Maneuvering.

URI

http://etd.lib.metu.edu.tr/upload/12624473/index.pdf
https://hdl.handle.net/11511/44149

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

Analysis of Aircraft Survivability Against Fragmenting Warhead Threat Konokman, Hüseyin Emrah; Kayran, Altan; KAYA, MUSTAFA (2014-01-17) The article presents the methodology of the aircraft survivability analysis considering vulnerability of the aircraft against fragmenting warhead threat. The initial step of the survivability analysis against a fragmenting warhead threat is to position the target and the warhead in proper coordinate systems for the calculation of warhead-target engagement. Once the warhead detonates at a miss distance from the target, the motions of the fragments are calculated considering the drag and the gravity forces an...
Static and Dynamic Aeroelastic Analysis of a Very Light Aircraft Demirer, Halime Gül; Kayran, Altan (2021-09-08) Aircraft design processes need to ensure that the aircraft will be aeroelastically stable within its operational envelope. This paper presents an overview of the static aeroelastic analysis results, flutter analysis and gust response analysis results of a very light aircraft. MSC.FlightLoads and MSC.Nastran are used for aeroelastic modeling and analysis. Aerodynamic calculations are based on the Doublet-Lattice Method (DLM), the aerodynamic theory employed by Nastran for subsonic flows. DLM requires all lif...
Static and dynamic aeroelastic analysis of a very light Aircraft Demirer, Halime Gül; Kayran, Altan; Department of Aerospace Engineering (2021-9-10) Aircraft design processes need to ensure that the aircraft is aeroelastically stable within its operational envelope. This thesis presents an overview of the static aeroelastic, flutter and gust response analysis of a very light aircraft. MSC.FlightLoads and MSC.Nastran are used for aeroelastic modeling and analysis. The methods to be used in the aeroelastic analysis of the VLA are tested on the AGARD 445.6 wing, and the results are in good agreement with the literature. Aeroelastic model corrections such a...
Development of a method for maximum structural response prediction of a store externally carried by a jet fighter Kaplan, Engin Metin; Acar, Erdem; Özer, Mehmet Bülent (2021-01-01) Experimental structural response of equipment mounted in store carried externally by jet type aircraft is investigated, predicted and compared with responses suggested by military standards in this study. A representative store which is similar to Mark-83 warhead with guidance units in terms of mass and geometry is used in this study. The main scope of this study is to evaluate the structural response proposed by military standards with real test conditions and also suggest a new method with an artificial n...
Application of frequency-domain linearized Euler solutions to the prediction of aft fan tones and comparison with experimental measurements on model scale turbofan exhaust nozzles Özyörük, Yusuf (Elsevier BV, 2011-08-01) Although it is widely accepted that aircraft noise needs to be further reduced, there is an equally important, on-going requirement to accurately predict the strengths of all the different aircraft noise sources, not only to ensure that a new aircraft is certifiable and can meet the ever more stringent local airport noise rules but also to prioritize and apply appropriate noise source reduction technologies at the design stage. As the bypass ratio of aircraft engines is increased - in order to reduce fuel c...

Citation Formats

B. E. Akmenek, “Testing of a flight envelope protection system for fly-by-wire aerial vehicles,” Thesis (M.S.) -- Graduate School of Natural and Applied Sciences. Aerospace Engineering., Middle East Technical University, 2019.