Design Analysis of Ducted Propeller for Bicopter Drone Propulsion

Priatmoko, M. R.; Nirbito, Wahyu

doi:10.1088/1757-899x/685/1/012008

Cited by 5 publications

(4 citation statements)

References 2 publications

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“…It comprises two motor and propeller arrangements to create thrust for generating lift for aerial vehicles. Bicopters are controlled by generating thrust through tilting of propeller arrangement in a calculated manner [23]. An American Bi-copter V-22 Osprey is an aerial vehicle with a tilt-rotor system for taking off in an upward direction.…”

Section: Wing Structurementioning

confidence: 99%

Design and Analysis of Hybrid Fixed-Wing Type Flying Robot

Maity

Mishra

Pattnaik

et al. 2022

Wireless Communications and Mobile Computing

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With the advent of disruptive technologies, unmanned aerial vehicles have seen substantial growth over the past few years. The market for flying robots is increasing drastically, and they are getting used in various sectors. This paper is aimed at discussing the novel design of a hybrid fixed-wing type flying robot in which both fixed-wing and rotary-wing concepts are combined so that stable flight with vertical takeoff can be possible. Our design proposes a compact structure that can be efficiently used in indoor applications. We have also discussed its structural analysis, the model’s stability, the CFD analysis, and the vibrational analysis of the designed structure. The objective is to design an effective compact flying robot system that will be used for medical applications and need to carry a payload of a minimum of 2 kg with good aerodynamic performance. The aerodynamic model required for a hybrid fixed-wing type flying robot has been developed, and the static stability of the model has been evaluated in the paper.

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Section: Wing Structurementioning

confidence: 99%

Design and Analysis of Hybrid Fixed-Wing Type Flying Robot

Maity

Mishra

Pattnaik

et al. 2022

Wireless Communications and Mobile Computing

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“…Control (extended active fault-tolerant control) method [62]. [73] x x x Liben 2021 [74] x x x x x Zhao 2021 [75] x x x x Duan 2020 [76] x x x x x Liu 2020 [77] x Marcolini 2020 [78] x x x x Ren 2020 [79] x x x x Anzai 2019 [80] x x x Dai 2019a [81] x x x x x x Guan 2019 [82] x x x x x Guiatni 2019 [83] x x x x x x Liben 2019 [84] x x x x x Priatmoko 2019 [85] x x x x Qian 2019 [86] x x x x x x De Simone 2018 [87] x x x x x x Kang 2018 [88] x x x x x x x Liu 2018 [89] x x x x Mallavalli 2018 [90] x x x x Xu 2018 [91] x x x x x x…”

Section: Literature Analysismentioning

confidence: 99%

“…Considering the UAV type, the focus of most of the studies was divided between fixed-wing UAVs and multirotor vehicles. Within the latter sub-category, fourteen papers explicitly referred to quadrotor systems [16,24,31,32,34,35,43,44,50,79,83,90,105,106], two to hexarotor UAVs [64,133], one to bicopters [85] and one to octocopter drones [108], respectively. Several papers did not specifically state a UAV type target in terms of architecture configuration, whereas others focused more properly on the drone characteristics, as the specific performance that the UAV needed to assure, or the kind of mission in which the system was expected to be engaged [36,[40][41][42].…”

Section: Uav Typesmentioning

confidence: 99%

Review of Propulsion System Design Strategies for Unmanned Aerial Vehicles

et al. 2021

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The design of the propulsion system for Unmanned Aerial Vehicles (UAVs) demands an inclusive multidisciplinary approach from the earliest design phases, since every design choice strictly affects and is affected by the overall working conditions. This paper presents a review of the scientific literature focused on the design methods applied in defining and sizing the propulsion system of drones. The analysis, performed with a systematic approach, evaluated 123 papers according to two custom classification taxonomies, which investigated respectively the primary aim and specific content of the works. Finally, literature indications and hints were combined into an integrated framework for the functional design of the propulsion system of UAVs. The procedure aimed to support the designer in the preliminary selection of the propulsion candidates and the quick sizing of the supply system, during the first phases of the design process. According to the literature, design methods dramatically change depending on the expected applications and working conditions of UAVs, so that the detailed design of specific drone elements and propulsion components represents the focus of most of the papers in this field.

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“…Basically, UAV is a flying vehicle that can be remotely or programmed to conduct autonomous task [1] which do not need a pilot to control instead all people who learned to fly the UAV start at young age. Previously, the usage of UAV only limited for military purpose but nowadays, the function becomes variety that can be used for other activities such as photography, regional mapping and entertainment media [2]. A few features offered such as small size, low cost and easy manoeuvrability of these system have made them potential in avionics industry [3] and become the most useful avionic in the 4 th industrial revolutionary.…”

Section: Introductionmentioning

confidence: 99%

Airflow Characteristic of UAV Quadcopter Propeller Blade Using Computational Fluid Dynamics (CFD)

Azizan¹,

Sapit²

2022

PAAT

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In this study, the main focus is to study of air flow characteristic of UAV quadcopter propeller at incorporate blade profile using variableangle of attack (AoA)and revolution per minute (RPM) with its twisted blade using Computational Fluid Dynamics (CFD) / Ansys tool. Three propellers have been designed which Propeller 1 is untwisted while Propeller 2 and 3 twisted at certain angle. Three speeds which are 4000 rpm, 6000 rpm and 8000 rpm have been set for each propeller are being analysed using ANSYS Fluid Flow (fluent). The result shows the different thrust force generated by three propellers and Propeller 2 (33.6757 N) has the highest thrust force generated compared to Propeller 1 and 3 especially at 8000 rpm. This is due to the suitable twisting angle profile that has been set at the Propeller 2at this operating speed. For comparison, Propeller 3 produce the highest thrust force of 18.44Nat 6000 rpmexceeding Propeller 2 which is 17.81 N.To summarize, each propeller blade profile has a distinctive aerodynamic performance and should be adopted by matching the flight operating condition. Higher rpmgenerateshigherthrust force, and increaselift and drag coefficient.

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Design Analysis of Ducted Propeller for Bicopter Drone Propulsion

Cited by 5 publications

References 2 publications

Design and Analysis of Hybrid Fixed-Wing Type Flying Robot

Design and Analysis of Hybrid Fixed-Wing Type Flying Robot

Review of Propulsion System Design Strategies for Unmanned Aerial Vehicles

Airflow Characteristic of UAV Quadcopter Propeller Blade Using Computational Fluid Dynamics (CFD)

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