Conceptual Design and Multi-Disciplinary Computational Investigations of Multirotor Unmanned Aerial Vehicle for Environmental Applications

Abstract

This study focuses on establishing a conceptual design for a multirotor unmanned aerial vehicle (UAV). The objectives of this octocopter are to reduce the number of flight cancelations and car accidents owing to low-visibility issues and to improve abnormal environmental conditions due to the presence of smoke. The proposed octocopter contains a convergent–divergent [CD] duct-based storage tank, which provides a platform to store saltwater and allows it to fly in foggy zones. Fine saltwater is sprayed from the octocopter and dispersed into the low clouds, thereby altering the vapor’s microphysical processes to break it up and improve visibility. The nature of the seawater and its enhanced fluid properties, due to the involvement of octocopter, creates the fluid flow mixing between atmospheric fluids and spraying particles, which increases the settling of foggy and smokey content groundward. For deployment, the conceptual design of the octocopter was initially constructed through analytical approaches. Additionally, three unique historical relationships were created. The standard engineering approaches involved in this work were stability analysis through MATLAB and fluid-property analysis through computational fluid dynamics (CFD) cum multiple reference frame (MRF) tools. The systematic model of this octocopter was developed by CATIA, and thereafter CFD and fluid–structure-interaction (FSI) analyses were computed, in ANSYS Workbench, on the octocopter for various environmental conditions. The aerodynamic forces on the drone, the enhancement of dynamic pressure by the presence of high amounts of rotors and nozzle sprayer, suitable material to resist aerodynamic loadings, and tests on the efficiency of the controller and its electronic components were investigated in detail. Finally, the proposed octocopter-based dynamic system was conceptually constructed.

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

“…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.…”

“…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,…”

“…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.…”

“…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.…”

“…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.…”