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An analysis of phugoid oscillations of unmanned flying wing

Mioduska P.

Journal of KONES

2016

Vol. 23, No. 2

247--254

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.

Structural weight estimation of a flying wing with a pressurized wing box

Rodriquez C., Martinez-Val R., Gutierrez L.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

2000

nr 10

177-182

The present paper will introduce a prediction method that will allow for estimation of the structural weight of a transport flying with an approximate capacity of 300 passengers. The flying wing payload will be located between the front and rear spars, and up to half the span approximately, which implies that the study of the wing structure will have two different parts; i.e., the external structure that will be of conventional architecture apart from its dimensions that will be bigger and the internal structure, no conventional, where the torsion box will be pressurized and with all the equipment required for passenger and, cargo transportation.