Design and Innovative Integrated Engineering Approaches Based Investigation of Hybrid Renewable Energized Drone for Long Endurance Applications

Abstract

At present, surveillance is attracting attention in the field of UAV development. In particular, border surveillance plays a vital role in obtaining the required data around the border and for assisting in military operations. The primary function of this Hybrid UAV (VTOL and Fixed Wing) is to provide prerequisite data, captured during day/night surveillance, to the respective database. One of the primary problems that arise in border patrolling is the use of the UAV under different environmental conditions, thereby reducing its endurance firmly. In addition to the surveillance equipment, energy harvesting techniques are involved in solving the problem of endurance. The piezoelectric energy harvester and solar panels are added to harvest electrical energy in the UAV. Based on this application, the conceptual design of the Hybrid UAV, based on nature, was designed and investigated theoretically, as well as computationally. A series of analysis, which includes Computational Fluid Dynamics, Finite Element Analysis and Analytical approach, was used to determine the energy harvested from the energy harvester. This work confirms the proposed integrated engineering approach for the estimation of renewable energy, via PVEH patches, and the same approach is thus offered to researchers for subsequent applications. Additionally, a hybrid energy idea for newly developed drones was proposed in this work. This concept will be extensively used in the unmanned aircraft system sectors.

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.…”

“…As similar as previously shown calculations, the other sectional calculations are determined. The complete design data of main rotor blade is listed in Table 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).…”