Kinematic synthesis of flight control systems for light aircrafts

Download
2002-01-01
Yaman, Yavuz
Soylemez, E
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.
AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY

Suggestions

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.