A low cost prototyping approach for design analysis and flight testing of the TURAC VTOL UAV

Aktas, Yucel Orkut; Ozdemir, Ugur; Dereli, Yasin; Tarhan, Ahmed Farabi; Cetin, Aykut; Vuruskan, Aslihan; Yüksek, Burak; Cengiz, Hande; Basdemir, Serkan; Ucar, Mesut; Genctav, Murat; Yukselen, Adil; Özkol, İbrahim; Kaya, Metin O.; Tsourdos, Antonios

doi:10.1109/icuas.2014.6842354

Cited by 19 publications

(13 citation statements)

References 7 publications

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“…So, the induced velocity can be approximated by momentum theory as given in Eq. (14). According to the available rotorcraft forward flight performance equations, 22,23 the non-ideal induced power term during transition flight can be formulated as given by Eq.…”

Section: B Transition Flight Sizingmentioning

confidence: 99%

“…Despite the importance and the need for developing TA, the design problems associated with such type of aircraft has hitherto received very little attention in the research literature. Even though most previously developed aircraft are unstable, [12][13][14] no attention has been paid to develop/discuss methodologies to design stable TA. This paper presents the first step in the design of TA, TA preliminary design, and some of the challenges accompanying this process.…”

Section: Introductionmentioning

confidence: 99%

“…In contrast to using historical data, other studies have proposed to use momentum theory to calculate the power loading in designing tiltwing and other transitional type of aircraft. The first study 20 designed and tested a tilt-wing UAV, whereas the others to maintain flight 13,14 did the same process for a transitional UAV with two tilt-motors in the front, and a fixed coaxial ducted fan in the rear. Unfortunately, the later UAV is also inherently unstable and when in operation, it heavily relies on the flight control system.…”

Section: Introductionmentioning

confidence: 99%

“…Unfortunately, the later UAV is also inherently unstable and when in operation, it heavily relies on the flight control system. 13,14 Although momentum theory is considered better than historical data in estimating the power, it can only be used to calculate the required power during the hovering mode, which is thought to be not sufficient for all the three flight phases in a typical TA mission. Based on previous work, which has shown that it is possible to fly transitional tiltrotor aircraft in both modes (VTOL and fixed-wing) with only one aircraft configuration.…”

Section: Introductionmentioning

confidence: 99%

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Design methodology for hybrid (VTOL + Fixed Wing) unmanned aerial vehicles

Kamal

Ramírez-Serrano

2018

AAOAJ

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The evolution in the missions' complexity of both military aircraft and Unmanned Aerial Vehicles (UAVs) and the increase in civilian air-traffic, with limited runways, have led to the development of a new category of aircraft called Transitional Aircraft (TA). The goal of TA is to take advantages of both the characteristics of fixed-wing aircraft, like high speed, range and endurance, and of rotorcraft such as hovering, low-speed flight and Vertical Takeoff and Landing (VTOL). Despite the abundant knowledge on designing both fixed-wing aircraft and rotorcraft, designing TA has proven to be a challenging process and poorly understood. Currently there is no well accepted generic methodology that can be used for designing this type of aircraft such as tiltrotor systems due to the fact that there are numerous challenges regarding the selection of the proper TA configuration. Although somewhat effective, previously developed TA suffer from problems regarding the mutual aerodynamic interaction that occurs during the transition flight phase when the aircraft transitions between fixed-wing and rotorcraft flight modes. In order to cope with these problems, this paper presents a preliminary design methodology for TA with a set of newly developed mathematical formulations that integrate traditional fixed-wing and rotorcraft aircraft design methodologies into a comprehensive TA design methodology. Due to the potential large set of TA configurations that exist and can be proposed, this paper focuses on transitional tiltrotors which have been identified as critical importance. The proposed TA design approach is used to analyze a hypothetical TA configuration under development by the authors of this paper showing that the proposed design approach can be used to prevent some of the frequent shortcomings found on previously developed aircraft. The methodology is able to assist TA designers obtain adequate power, wing, and rotor disc loadings using the developed sizing mathematical formulations for tiltrotor aircraft based on integrating the performance requirements in the fixed-wing, rotorcraft, and transition flying modes.

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Section: B Transition Flight Sizingmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Design methodology for hybrid (VTOL + Fixed Wing) unmanned aerial vehicles

Kamal

Ramírez-Serrano

2018

AAOAJ

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“…Firt of all, Convertiplanes category regroup those aerial vehicles that take off, cruise, hover and land with the aircraft reference line remaining horizontal. Respect to this class, there exist several vehicles implementing the idea such as FireFLY6 [2] and TURAC [3]; and also projects researching in this direction [4,5]. Second, a Tail-Sitter is an aircraft that takes off and lands vertically on its tail and the whole aircraft tilts forward using differential thrust or control surfaces to achieve horizontal flight.…”

Section: Introductionmentioning

confidence: 99%

Motion Equations and Attitude Control in the Vertical Flight of a VTOL Bi-Rotor UAV

et al. 2019

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This paper gathers the design and implementation of the control system that allows an unmanned Flying-wing to perform a Vertical Take-Off and Landing (VTOL) maneuver using two tilting rotors (Bi-Rotor). Unmanned Aerial Vehicles (UAVs) operating in this configuration are also categorized as Hybrid UAVs due to their ability of having a dual flight envelope: hovering like a multi-rotor and cruising like a traditional fixed-wing, providing the opportunity of facing complex missions in which these two different dynamics are required. This work exhibits the Bi-Rotor nonlinear dynamics, the attitude tracking controller design and also, the results obtained through Hardware-In-the-Loop (HIL) simulation and experimental studies that ensure the controller’s efficiency in hovering operation.

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