Vertical take off and landing with fixed rotor

Orbea, David; Moposita, Jessica; Aguilar, Wilbert G.; Paredes, Manolo; Reyes, Rolando P.; Montoya, Luis

doi:10.1109/chilecon.2017.8229691

Cited by 16 publications

(9 citation statements)

References 16 publications

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“…Figure 9 presents the lift and drag coefficients as the functions of angle of attack (AoA) for Re = 237 000. Although the maximal lift coefficient is low comparing to other conceptual studies [44], especially dedicated for the same purpose [16], the designed UAV has satisfactory parameters from the project aims point of view. The zero lift condition appears for AoA equal to −1 ∘ whereas the stall point is achieved for 12 ∘ .…”

Section: Cfd Simulationsmentioning

confidence: 83%

See 1 more Smart Citation

Construction Prototyping, Flight Dynamics Modeling, and Aerodynamic Analysis of Hybrid VTOL Unmanned Aircraft

Czyba

Lemanowicz

Gorol

et al. 2018

Journal of Advanced Transportation

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A challenging issue associated with fixed-wing Unmanned Aerial Vehicles (UAVs) is that these vehicles are often not appropriate for operating effectively in limited airspace. This problem emerges especially in urban environment where the usage of a runway is not possible, and UAVs usually have to fly at a relatively low speed and altitude. The development of a vertical take-off and landing (VTOL) fixed-wing plane is a promising trend which hopefully will solve this issue. This paper presents the design process of an unmanned vertical take-off and landing aircraft including prototyping of the airframe construction and mathematical modeling as well as computational fluid dynamics (CFD) simulations. The designed system is to be a hybrid platform, for which different operating modes correspond to the vertical flight, transition, and spatial flight in the airframe system. The paper discusses an iterative design process of the platform with emphasis on CAD design and aerodynamic analysis for particular flight modes. The operating prototype is presented and future plans for platform improvement are discussed.

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Section: Cfd Simulationsmentioning

confidence: 83%

“…Over the last five years, many hybrid VTOL structures have been created [1,[13][14][15][16]. One of them is Tilt-Rotor [17][18][19][20], where multiple rotors are mounted on rotating shafts or nacelles.…”

Section: Introductionmentioning

confidence: 99%

Construction Prototyping, Flight Dynamics Modeling, and Aerodynamic Analysis of Hybrid VTOL Unmanned Aircraft

Czyba

Lemanowicz

Gorol

et al. 2018

Journal of Advanced Transportation

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show abstract

“…Lastly, a common class of hybrid UAVs is formed by quadplanes [21][22][23][24][25] which are also referred to as dual-systems (See example in Figure 1). The quadplane has a static configuration with the hover rotors and the fixed wings in the same plane.…”

Section: Introductionmentioning

confidence: 99%

“…Over-actuation and conflicting requirements are often dealt with by using different actuators and switching controllers during specific flight phases, and only briefly combining them during a transition phase between hovering and horizontal flight. [21][22][23][24] Incremental Non-linear Control Allocation (INCA) has been proposed to solve over-actuation. The theoretical study by Stolk 26 applied it to the Lockheed Martin Innovative Control Effector aircraft.…”

Section: Introductionmentioning

confidence: 99%

Extended incremental non-linear control allocation (XINCA) for quadplanes

Karssies

Wagter

2022

International Journal of Micro Air Vehicles

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Hybrid UAVs have gained a lot of interest for their combined vertical take-off & landing (VTOL) and efficient forward flight capabilities. But their control is facing challenges in over-actuation and conflicting requirements depending on the flight phase which can easily lead to actuator saturation. Incremental Non-linear Control Allocation (INCA) has been proposed to solve the platform’s control allocation problem in the case of saturation or over-actuation by minimizing a set of objective functions. This work demonstrates INCA on quadplanes, an in-plane combination between a quadrotor and a conventional fixed-wing, and proposes an extension to control the outer loop. The novel controller is called Extended INCA (XINCA) and adds the wing orientation as a force-generating actuator in the outerloop control optimization. This leads to a single controller for all flight phases that avoids placing the wing at negative angles of attack and minimizes the load on hover motors. XINCA has low dependence on accurate vehicle models and requires only several optimization parameters. Flight simulations and experimental flights are performed to demonstrate the performance.

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“…Over recent years, various kinds of UAV concepts have been developed [1][2][3][4][5][6][7][8][9][10][11][12]. The three most common types of UAVs are the rotary-wing UAVs, the fixed-wing (FW) UAVs, and the mixed UAVs known as hybrid UAVs.…”

Section: Introductionmentioning

confidence: 99%

Design and Structural Analyses of a Reciprocating S1223 High-Lift Wing for an RA-Driven VTOL UAV

2021

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In the design stage of an aircraft, structural analyses are commonly employed to test the integrity of the aircraft components to demonstrate the capability of the structural elements to withstand what they are designed for, as well as predict potential failure of the components. This research focused on the structural design and analysis of a high-lift, low Reynolds number airfoil profile, the Selig S1223, under reciprocating inertial force loading, to determine the feasibility of its use in a new reciprocating airfoil (RA) driven VTOL UAV. The material selected for the wing structures including ribs, spars, and skin, was high-strength carbon fiber. The wing was designed in SolidWorks, while finite element analysis was performed with ANSYS mechanical in conjunction with the inertia forces due to the reciprocating motion of the wing and the lift and drag forces that were derived from the aerodynamic wing analyses. The structural stress and strain determined under the loading conditions were satisfactory and the designed wing could sustain the high reciprocating inertia forces in the RA-driven VTOL UAV module. The results of this study indicate that the Selig S1223 airfoil profile, due to its superior performance at low Reynolds numbers, high-lift, and reduced noise characteristics at low angles of attack, combined with the use of the high strength carbon fiber, proves to be an excellent choice for this RA-driven aircraft application.

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Vertical take off and landing with fixed rotor

Cited by 16 publications

References 16 publications

Construction Prototyping, Flight Dynamics Modeling, and Aerodynamic Analysis of Hybrid VTOL Unmanned Aircraft

Construction Prototyping, Flight Dynamics Modeling, and Aerodynamic Analysis of Hybrid VTOL Unmanned Aircraft

Extended incremental non-linear control allocation (XINCA) for quadplanes

Design and Structural Analyses of a Reciprocating S1223 High-Lift Wing for an RA-Driven VTOL UAV

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