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

Imumbhon, Johnson O.; Alam, Mohammad Didarul; Cao, Yiding

doi:10.3390/aerospace8080214

Cited by 12 publications

(8 citation statements)

References 10 publications

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“…Due to the drone carrying detectors for low altitude search, altitude within 5-20 m, flight speed range of 5-15 m/s, the initial chord length c is 80 mm, r is the airflow density as 1.225 kg/m 3 (Imumbhon et al, 2021). According to the preliminary selected data, according to the above formula ( 16), the maximum thrust of the designed propeller is 60.51 N. According to the maximum take-off weight of 30 kg, the overall lift generated by the coaxial rotor is estimated to be 363.06 N, about 37 kg, which meets the design requirements.…”

Section: Airfoil Designmentioning

confidence: 99%

Design and aerodynamic characteristics analysis of propellers for a novel rescue unmanned aerial vehicle

Guan,

2023

AEAT

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Purpose To solve the shortcomings of existed search and rescue drones, search and rescue the trapped people trapped in earthquake ruins, underwater and avalanches quickly and accurately, this paper aims to propose a four-axis eight-rotor rescue unmanned aerial vehicle (UAV) which can carry a radar life detector. As the design of propeller is the key to the design of UAV, this paper mainly designs the propeller of the UAV at the present stage. Design/methodology/approach Based on the actual working conditions of UAVs, this paper preliminarily estimated the load of UAVs and the diameters of propellers and designed the main parameters of propellers according to the leaf element theory and momentum theory. Based on the low Reynolds number airfoil, this paper selected the airfoil with high lift drag ratio from the commonly used low Reynolds number airfoils. The chord length and twist angle of propeller blades were calculated according to the Wilson method and the maximum wind energy utilization coefficient and were optimized by the Asymptotic exponential function. The aerodynamic characteristics of the designed single propeller and coaxial propeller under different installation pitch angles and different installation distances were analyzed. Findings The results showed that the design of coaxial twin propellers can increase the load capacity by about 1.5 times without increasing the propeller diameter. When the installation distance between the two propellers was 8 cm and the tilt angle was 15° counterclockwise, the aerodynamic characteristics of the coaxial propeller were optimal. Originality/value The novelty of this work came from the conceptual design of the new rescue UAV and its numerical optimization using the Wilson method combined with the maximum wind energy utilization factor and the exponential function. The aerodynamic characteristics of the common shaft propeller were analyzed under different mounting angles and different mounting distances.

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Section: Airfoil Designmentioning

confidence: 99%

Design and aerodynamic characteristics analysis of propellers for a novel rescue unmanned aerial vehicle

Guan,

2023

AEAT

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“…Schematic illustration of the design and simulation procedure of this study. (Cao 2019;Imumbhon et al 2021). These values indicate the RA wing performance is superior to rotary wings but similar to fixed wings.…”

Section: Selig S1223 Airfoil Summarymentioning

confidence: 99%

“…The literature review on the RA wing revealed that the RA VTOL aircraft is at a very early developmental stage (Cao 2019;Cao 2020;Alam and Cao 2021;Imumbhon et al 2021). Nevertheless, RA-driven VTOL aircraft (Cao 2019;Cao 2020) may have the potential to overcome the many challenges discussed above.…”

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confidence: 99%

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Structural and CFD Analyses of a Reciprocating-Airfoil (RA) driven UAV Wing under Maximum Lift and Inertia Forces.

2022

Self Cite

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The Reciprocating-Airfoil (RA) driven vertical take-off and landing (VTOL) aircraft is a new aircraft concept that utilizes the reciprocating motion of the wings to provide lift for take-off and landing. The RA wings are shaped like the wings of a fixed-wing airplane and work as fixed wings during the cruise. The wing undergoes substantial linear motion during the take-off and may generate lift similar to a fixed-wing aircraft. The unique structural characteristics of reciprocating wings are their high inertia and lifting force loadings. This study aims to conduct an internal structural analysis of the wing under the maximum lift and inertia force to validate the wing's performance. The reciprocating motion of the wing in a stroke was analyzed to determine its maximum speed in the stroke and its inertia force loading in conjunction with a reciprocating driver. A 3D computational fluid dynamic (CFD) analysis was conducted at the highest angle of attack (AoA) and the determined maximum speed to obtain maximum lift and drag. The results of a finite element analysis (FEA) revealed acceptable stresses, demonstrating a safe load-carrying capacity of the wing structure which may ensure the suitability of the wing for integration with the RA UAV module.

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“…Numerous researchers have looked into using the S1223 for high-lift and relatively slow flight applications due to its relatively high maximum lift coefficient [7]. The S1223 airfoil has a high lift and a low Reynolds number, making it ideal for short-field aircraft operations.…”

Section: Literature Reviewmentioning

confidence: 99%

Aerodynamics of a Modified High-Lift Low Reynolds Number Airfoil: Preliminary Analysis

Mohamad¹,

Noh²,

Nasir³

et al. 2022

IJETAE

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Airfoil selection is a crucial phase in the design of a small unmanned fixed-wing aircraft to allow a minimum size and weight of the lifting surfaces. The present study analyzesairfoils to be used in low operating Reynolds number unmanned aerial vehicles (UAV) using XFLR5 software, which was validated against wind tunnel data. Three baseline airfoils were investigated, namely NACA4412, Miley M06-13- 128 and Selig S1223. The best performing airfoils are then modified using the inverse airfoil design method to improve their performance in cruising flight. The modified airfoil resulted in larger leading edge radius and slightly thicker chord of the airfoil compared to the baseline airfoil. In general, the modified airfoil showed an improvement in stall characteristic, lift and drag coefficients in the post-stall regime, and a lower magnitude of moment coefficient for almost all investigated angles of attack compared to the baseline airfoil.

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

Cited by 12 publications

References 10 publications

Design and aerodynamic characteristics analysis of propellers for a novel rescue unmanned aerial vehicle

Design and aerodynamic characteristics analysis of propellers for a novel rescue unmanned aerial vehicle

Structural and CFD Analyses of a Reciprocating-Airfoil (RA) driven UAV Wing under Maximum Lift and Inertia Forces.

Aerodynamics of a Modified High-Lift Low Reynolds Number Airfoil: Preliminary Analysis

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