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International Journal for Research Trends and Innovation
International Peer Reviewed & Refereed Journals, Open Access Journal
ISSN Approved Journal No: 2456-3315 | Impact factor: 8.14 | ESTD Year: 2016
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Impact Factor : 8.14
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| Paper Title: | Vibration and Explicit Analysis for impact test of a Heavy-Lift Hexacopter Drone |
| Authors Name: | Boda Devender , Dr. K. Gurubrahmam |
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IJRTI_213635
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| Published Paper Id: | IJRTI2606101 |
| Published In: | Volume 11 Issue 6, June-2026 |
| DOI: | |
| Abstract: | Unmanned Aerial Vehicles (UAVs) are increasingly deployed in aerial surveillance, precision agriculture, environmental monitoring, disaster management, logistics and infrastructure inspection. In all of these roles the structural frame governs flight stability, payload capability, vibration resistance and impact durability, so the selection of a lightweight material and the verification of its structural performance are critical to safe operation. This paper presents the design, parametric modelling and finite element analysis (FEA) of a heavy-lift hexacopter (six-rotor) drone frame made of Carbon Fibre Reinforced Polymer (CFRP). A three-dimensional model of the 800 mm-diagonal frame — central hexagonal body, six tubular arms, motor-mounting pads and a landing structure — was developed in SolidWorks 2025 and imported into ANSYS Workbench for simulation, with the frame modelled as an orthotropic Epoxy Carbon UD laminate of total frame-and-motor mass ≈ 1.84 kg. Static structural analysis was carried out at four payload levels (25, 50, 75 and 100 N) on a mesh-independent model of ≈ 1.05 million elements, and the CFRP frame was compared against an identical Nylon 6/6 frame. Modal analysis extracted the first six natural frequencies; harmonic response analysis (0–700 Hz, 100 N) evaluated the steady-state dynamic response; and two explicit-dynamic analyses assessed the landing structure under a gravity-settling case and a 1 m hard-drop impact. The maximum Von-Mises stress rose linearly from 24.0 MPa at 25 N to 96.0 MPa at the critical 100 N load, where the maximum deformation was 1.387 mm and the factor of safety (FoS) was 15.63 — about 10.4× the required minimum of 1.5. At the same load the Nylon 6/6 frame failed (FoS = 0.83). The first six natural frequencies (192.49–687.81 Hz) lie well above the motor-excitation range; the harmonic analysis gave a maximum stress of 85.78 MPa and a deformation of only 0.077 mm. The 1 m drop produced a peak stress of 385.84 MPa against the 1500 MPa CFRP strength (FoS = 3.89). The results establish that the proposed lightweight CFRP hexacopter frame is structurally safe, dynamically stable and impact-resistant, making it well suited to reliable heavy-lift UAV applications |
| Keywords: | UAV, Hexacopter Drone, CFRP, Finite Element Analysis, Static Structural Analysis, Modal Analysis, Harmonic Response Analysis, Explicit Dynamic Analysis, ANSYS Workbench, Composite Materials. |
| Cite Article: | "Vibration and Explicit Analysis for impact test of a Heavy-Lift Hexacopter Drone", International Journal for Research Trends and Innovation (www.ijrti.org), ISSN:2456-3315, Vol.11, Issue 6, page no.a946-a949, June-2026, Available :http://www.ijrti.org/papers/IJRTI2606101.pdf |
| Downloads: | 00093 |
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2456-3315 | IMPACT FACTOR: 8.14 Calculated By Google Scholar| ESTD YEAR: 2016 An International Scholarly Open Access Journal, Peer-Reviewed, Refereed Journal Impact Factor 8.14 Calculate by Google Scholar and Semantic Scholar | AI-Powered Research Tool, Multidisciplinary, Monthly, Multilanguage Journal Indexing in All Major Database & Metadata, Citation Generator |
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Published Paper ID: IJRTI2606101
Registration ID:213635
Published In: Volume 11 Issue 6, June-2026
DOI (Digital Object Identifier):
Page No: a946-a949 Country: Bhadradri kothagudem, Telangana, India Research Area: Mechanical Engineering Publisher : IJ Publication Published Paper URL : https://www.ijrti.org/viewpaperforall?paper=IJRTI2606101 Published Paper PDF: https://www.ijrti.org/papers/IJRTI2606101 |
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ISSN: 2456-3315
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