Kinematic synthesis of flight control systems for light aircrafts

Download

index.pdf

Date

2002-01-01

Author

Yaman, Yavuz
Soylemez, E

Metadata

Show full item record

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

Item Usage Stats

149
views

0
downloads

In this paper, kinematic synthesis of a planar flight control system mechanism has been conducted for a light aircraft designed and built by TAL To achieve a simple construction, the four-bar linkages are used in the synthesis. Freudenstein's Method and Bloch's Method are utilized for analytical three and four bar position syntheses respectively. A case study of an elevator flight control system is presented.

Subject Keywords

Control systems, Aircraft

URI

https://hdl.handle.net/11511/41049

Journal

AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY

DOI

https://doi.org/10.1108/00022660210414985

Collections

Department of Aerospace Engineering, Article

Suggestions

OpenMETU
Core

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...
Data-Driven Model Discovery and Control of Lateral-Directional Fighter Aircraft Dynamics Öznurlu, Can; Uğur, Ömür; Çimen, Tayfun; Department of Scientific Computing (2022-8-26) The focus of this thesis is to control the lateral-directional motion of the fighter aircraft by using integral action based Model Predictive Control (MPC) where the model is obtained by data-driven model discovery method. Dynamic Mode Decomposition with Control (DMDc) is used as a model discovery technique based only on measurement data with no modeling assumptions. The model created using this technique is used for MPC and tested against noisy conditions. In addition, performance comparison of MPC with Cl...
Measurements of dynamic stability derivatives using direct forced oscillation technique Alemdaroglu, N; Iyigun, I; Altun, M; Quagliotti, F; Guglieri, G (2001-08-30) The subject of the experimental investigation presented in this paper is to measure the dynamic stability derivatives of a generic combat aircraft model in the Ankara Wind Tunnel by using the direct forced oscillation technique. The model, used for the tests is the AGARD, Standard Dynamic Model (SDM). The aerodynamic loads acting on the model are measured with a five component internal strain gauge balance placed inside the oscillating model. The paper presents the experimental set-up used to create the osc...
Single axis attitude controller design using pulse width modulated thruster Silik, Yusuf; Yaman, Ulaş (2019-05-01) This work consists of design and experimental validation of Pulse Width Modulation (PWM) scheme for a cold gas thruster system which is driven by on/off type of actuators. PWM scheme designed according to the characteristics of the on/off type of actuators obtained by the developed solenoid valve model and the experimentation. Angular position of the single axis rotational platform is controlled by the PWM scheme and the state feedback angular position controller. The PWM scheme and the angular position con...
Manufacturing and structural analysis of a lightweight sandwich composite UAV wing Turgut, Tahir; Kayran, Altan; Department of Aerospace Engineering (2007) This thesis work deals with manufacturing a lightweight composite unmanned aerial vehicle (UAV) wing, material characterization of the composites used in the UAV wing, and preliminary structural analysis of the UAV wing. Manufacturing is performed at the composite laboratory founded in the Department of Aerospace Engineering, and with hand lay-up and vacuum bagging method at room temperature the wing is produced. This study encloses the detailed manufacturing process of the UAV wing from the mold manufactur...

Citation Formats

Y. Yaman and E. Soylemez, “Kinematic synthesis of flight control systems for light aircrafts,” AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY, pp. 12–18, 2002, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/41049.