An analysis of phugoid oscillations of unmanned flying wing

• Autorzy: Mioduska P.

Identyfikatory

DOI

10.5604/12314005.1213599

• Języki publikacji: EN

Abstrakty

EN

The flying wing configuration has been considered by airplane designers for more than one hundred years. Tailless aircraft have been inspired by nature and its solutions. In present times, this configuration is used to design Unmanned Aerial Vehicle (UAV). This type of plane could serve personal, military and research purposes. The flying wing is characterized by large amount of payload space, smaller wetted area than conventional airplane and stealth capability. This makes, that it is widely applicable in rescue operations, geodetic and cartographic research, monitoring of natural resources, taking pictures or videos. Despite all the merits of tailless plane, it also has its downsides. The main problem of this type of aircraft is longitudinal stability. A conventional airplane can compensate the pitch moment of the wing with its horizontal tail but a flying wing is tailless. A slow decay of oscillations amplitude is the problem, which can be solved by active control or proper aerodynamic design. A combination of geometric characteristic such as sweep, taper, twist and location of vertical stabilizers along span, can lead to stable flying wing. In this article, the results of phugoid oscillations analysis of unmanned flying wing are presented. Research platform was X8-2, popular flying wing UAV, designed for First Person View (FPV) method to control the vehicle. The calculations were performed using 3D panel method. On the basis of calculations for three versions of the model aircraft, the dynamic characteristics were created. The analysis of longitudinal stability undertaken here has indicated propriety of applied changes in geometry.

Słowa kluczowe

EN

UAV; flying wing; longitudinal stability; phugoid oscillations

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2016
• Tom: Vol. 23, No. 2
• Strony: 247--254
• Opis fizyczny: Bibliogr. 7 poz., rys.

Twórcy

autor

Mioduska P.

• Institute of Aviation, Department of Aerodynamics and Flight Mechanics Krakowska Avenue 110/114, 02-256 Warsaw, Poland tel.: [phone] ext. 359, fax: [phone]

Bibliografia

• [1] Aeroelectronics X8 Flying Wing Datasheet, http://www.airelectronics.es/.
• [2] http://www.xflr5.com.
• [3] Deperrois, A., About stability analysis using XFLR5, November 2010. 253
• [4] Deperrois, A., Guidelines for XFLR5, XFLR5 Analysis of foils and wings operating at low Reynolds numbers.
• [5] Hurt, H. H., Jr., Aerodynamics for Naval Aviators, Skyhorse Publishing Inc, p. 286, New York 2012.
• [6] Whittenbury, J., Configuration design development of the Navy UCAS-D X-47B, Report No.: AIAA-2011-7041, 2011.
• [7] Wise, K., X-45 Program overview and flight test status, Report No.: AIAA-2003-6645, 2003. 254

Uwagi

PL

Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę.