Conceptual Design and Numerical analysis of an Unmanned Amphibious Vehicle

Mathaiyan, Vijayakumar; Vijayanandh, R.; Murugesan, Ramesh; Madasamy, Senthil Kumar; Gnanasekaran, Raj Kumar; Sivalingam, Sivaranjani; Jung, Dong Won

doi:10.2514/6.2021-1285

Cited by 16 publications

(55 citation statements)

References 19 publications

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“…The payload weight is assumed as 22.5 kg to carry the cleaner for air pollution at large terminals like railway stations, bus stands, temples, churches, etc., From Figure 1, the historical relationship between overall weight of RUAV and its payload weight has been framed that is given in Eq. 1 (Mathaiyan et al, 2021;Murugesan et al, 2021;Raja et al, 2021;Senthilkumar et al, 2021;Raja et al, 2022a;Vijayanandh et al, 2022a;Raja et al, 2022b;Raja et al, 2022c;Raja et al, 2022d;Raja M. K. et al, 2022;Wang et al, 2022;Raja et al, 2023 Based on the defence applications, the UAV's speed is assumed as 25 m/s and the atmospheric velocity is measured as 3 m/s.…”

Section: Figurementioning

confidence: 99%

“…Let us assume the thrust of the propeller is generated 100% greater than the overall weight of the rotary wing UAV, Thus, ϱA (V c + v i ).2v i 114*9.8101.2256*A (3 + 25).2*25 1119.6153. Finally, the diameter of the main rotor is estimated as 36 inch (Mathaiyan et al, 2021;Murugesan et al, 2021;Raja et al, 2021;Senthilkumar et al, 2021;Raja et al, 2022a;Vijayanandh et al, 2022a;Raja et al, 2022b;Raja et al, 2022c;Raja et al, 2022d;Raja M. K. et al, 2022;Wang et al, 2022;Raja et al, 2023). The power consumed is given by the product of the thrust and the total velocity through the rotor disk, that is,…”

Section: Figure 10mentioning

confidence: 99%

“…The typical relationship between mechanical power required and its subordinates of drone design parameters is given in Eq. 4 (Mathaiyan et al, 2021;Murugesan et al, 2021;Raja et al, 2021;Senthilkumar et al, 2021;Raja et al, 2022a;Vijayanandh et al, 2022a;Raja et al, 2022b;Raja et al, 2022c;Raja et al, 2022d;Raja M. K. et al, 2022;Wang et al, 2022;Raja et al, 2023). Eq.…”

Section: Estimation Of Main Rotor's Pitchmentioning

confidence: 99%

“…5 is representing the dynamic thrust relationship for drone, wherein the design parameters of propellers are plays major role. To proceed further, the additional unknowns presented are reduced through comparative relationship approach (Mathaiyan et al, 2021;Murugesan et al, 2021;Raja et al, 2021;Senthilkumar et al, 2021;Raja et al, 2022a;Vijayanandh et al, 2022a;Raja et al, 2022b;Raja et al, 2022c;Raja et al, 2022d;Raja M. K. et al, 2022;Wang et al, 2022;Raja et al, 2023). Total deformation on half fuselage of RUAV with Epoxy-Carbon-Woven-Wet.…”

Section: Estimation Of Main Rotor's Pitchmentioning

confidence: 99%

“…For specific locations on the rotor blade, the pitch angle and chord length are determined using Formulae 7, 8. For sample calculation the 10% of radius, i.e., r = 1.8 inch, has been picked (Mathaiyan et al, 2021;Murugesan et al, 2021;Raja et al, 2021;Senthilkumar et al, 2021;Raja et al, 2022a;Vijayanandh et al, 2022a;Raja et al, 2022b;Raja et al, FIGURE 15 Equivalent stress on half fuselage of RUAV with GFRP and its associate materials.…”

Section: Estimation Of Pitch Angle and Chord Of The Main Rotormentioning

confidence: 99%

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Design and advanced computational approaches based comprehensive structural parametric investigations of rotary-wing UAV imposed with conventional and hybrid computational composite materials: A validated investigation

Raja¹,

AL-bonsrulah²,

Gnanasekaran³

et al. 2023

Front. Mater.

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This work aims to design a rotary-wing unmanned aerial system (RUAS) that monitors the pollutants and minimizes their concentration in the atmosphere. This RUAS could be well suited for implementation in cities such as New Delhi and Ghaziabad, where air pollution is a major concern. This RUAV’s well-thought-out design and use would be good for the environment also a step forward in the technology of UASs. Therefore, an advanced approach in design as well as innovative computational composite materials development based on structural analysis of this RUAS has been made. The major components involved in this comprehensive investigation are the fuselage, main rotor and tail rotor of RUAS. The aerodynamic parameters on RUAS have been estimated through the advanced technique adopted computational fluid dynamics approach using ANSYS Fluent 17.2. The finite element analysis (FEA) of the RUAS imposed under two different approaches enforced on lightweight composite materials has been estimated through ANSYS Structural 17.2. Firstly, the advanced computational platform for the development of composite materials has been created through the ANSYS Composite Preprocessor tool 17.2, wherein computational moldings of the fuselages of RUAV are framed. The computational moldings are greatly supported and so the conventional polymer matrix composites, metal matrix based composites, and advanced hybrid composites are well prepared. A ll of these uniquely framed materials have undergone computational structural investigations, and the material suitable for RUAVs has thus been selected. The computational tests are validated with advanced experimental outcomes, which furthermore enhanced the reliability of this proposed work. Additionally, the main rotor and entire RUAV are also computationally investigated under aerodynamic loading conditions through fluid structure interaction (FSI) approach. At last, the suitable lightweight material for all the parts of RUAS is shortlisted through innovative integrated computational engineering analyses.

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