PSI - Issue 71

Prathamesh Patil et al. / Procedia Structural Integrity 71 (2025) 388–394

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The main technique used to produce the PLA parts of the UAV was Fused Deposition Modelling (FDM). This method allows for the creation of intricate designs, material efficiency, and quick production. To strike a balance between strength and weight, every PLA component was made using a 0.4 mm nozzle, a layer height of 0.2 mm and 30% infill density. To reduce delamination and improve structural integrity under operational loads, the print orientation was

adjusted for each part. 3. Drone Analysis

The analysis of drones plays a crucial role in validating the drone’s capability. This analysis encompasses various analyses including static structural, aerodynamic efficiency and vibrations. Each part of the frame has been analysed through simulations to find out the scope of improvement and to optimize it. The table below shows the boundary conditions applied in order to perform the analysis.

Table 2. Constraints for analysis

Thrust (N) Torque (N mm)

Battery Weight (N)

Pixhawk Weight (N)

GPS Weight (N)

Gravitational

Acceleration

m / s 2

12.16 9.81 As mentioned in Table 2, the constraints were applied to the drone frame and following results were obtained. 3.1 Transient Structural Analysis In ANSYS, a transient analysis was carried out with a time interval of 0.01 second and a total simulation period of 2 seconds. Simulated take-off and landing sequences were among the loading conditions that included a time-varying thrust profile. In order to understand the dynamic response to time dependent forces, transient analysis was performed. This analysis revolves around the drone’s behaviour during take -off, landing and performing flight manoeuvres. By simulating this we can analyse the points where the stress and deformation might occur, eventually leading to optimization of the design accordingly. 181.23 3.188 0.56 0.314

Fig.1. (a) Stress; (b) Strain

The above images show the stress and the total deformation of the frame. The maximum indices stress was found to be 1.1014 MPa and maximum deformation was 0.1682 mm.