Dynamic stability derivatives of a manuevering combat aircraft model

Bu deneysel çalışmanın amacı, salınım yapmakta olan jenerik bir savaş uçağı modelinin 'Forced Oscillation' tekniği kullanılarak statik ve dinamik kararlılık türevlerinin Ankara Rüzgar Tüneli 'nde bulunmasıdır. Salınım testleri için kullanılan model AGARD, Standart Dinamik Modelidir. Bu model bir çok NATO ülkesinde farklı ölçüm teknikleri kullanılarak rüzgar tünellerinin verifikasyonu için üretilmiştir. Bu model üzerine etki eden aerodinamik yükler, ölçüm sisteminin en önemli parçası olan beş bileşenli balans tarafından ölçülmektedir. Bu makalede çalışmada kullanılan; deney düzeneği, hareket kontrol ve ölçüm sistemi ile statik ve dinamik test sonuçları sunulmuştur.

The purpose of this experimental study 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, which is used for the oscillatory tests is known as the AGARD, Standard Dynamic Model (SDM) and is manufactured as a generic combat aircraft model to verify different measurement techniques in various wind tunnels of NATO countries. 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 oscillatory motion in pitch for the model and the related motion control and the data acquisition units to measure the dynamic loads, and discussed the results of the measurements.

Kaynakça

[1[ Avcı, S., May 2000, "Static and Forced Oscillatory Tests on a Generic Combat Aircraft Model in Ankara Wind Tunnel," M Sc. Thesis, Middle East Technical University, Ankara.

[2] Altun, M., February 2001, "Manufacturing, Assembly and Commissioning of an Oscillating Test Rig to Measure the Dynamic Stability Derivatives in the Ankara Wind Tunnel," M Sc. Thesis, Middle East Technical University, Ankara.

[3] Iyigün, I., March 2001, "Determination of Dynamic Stability Derivatives For a Generic Combat Aircraft Under Forced Oscillations," M Sc. Thesis, Middle East Technical University, Ankara.

[4] Beyers, M.E., and Moulton, B. E., June 1984 "Pitch and Yaw Oscillation Experiments on the SDM at Mach 0.6," LTR-UA-76, Ottawa, Canada.

[5] Guglieri, G., Quagliotti, F.B., May-June 1993, "Dynamic Stability Derivatives Evaluation in a Low-Speed Wind Tunnel," Journal of Aircraft, Volume 30, Number 3, pp. 421-423.

[6] Guglieri, G., Quagliotti, F. B., Scarabelli, P. L., 1993, "Static and Oscillatory Experiments on the SDM at Politecnico di Torino," Nota Scientifica E Tecnica N. 74/93, Forced Oscillation Technique-Reference Documentation, vol.3, Politecnico di Torino, DIASP, Italy.

[7] Ozdemir, E., 2000, "Calibration and Instrumentation of Ankara Wind Tunnel," M Sc. Thesis, Middle East Technical University, Ankara.

[8] Orlik-Rückemann, K. J., "Subsonic Aerodynamic Coefficients of the SDM at Angles of Attack up to 90°, Report LTR-UA-93," Forced Oscillation Technique-Reference Documentation, vol.3, Politecnico di Torino, DIASP, Italy.

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