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Drone strike analysis on windshield of a helicopter using finite element method
Shrestha, Yuwaraj
Shrestha, Yuwaraj
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2021-12
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Abstract
Mid-air collisions of manned rotorcrafts with Unmanned Arial Systems (UASs) or drones,
are a major risk to helicopters as they may result in significant loss of human life, injuries, and
property damages. The current Federal Aviation Regulation (FAR) for rotorcrafts are based on the
utilization of a 1.0 kg (2.2-lb) bird only. The aim of this research is to develop a methodology
which can be utilized to certify a helicopter for small UAS collision using computer-based
modelling and impact analysis of the most common drone, 1.2 kg (2.7-lb) quadcopter, on the
windshield of a typical helicopter.
In this study, meshing of detailed CATIA geometry of a 1.2 kg DJI Phantom III UAS is
done in the LS-PrePost, and then verified by simulating the free fall impact on a rigid plate and
comparing the result to the vertical drop test experiment at the WSU-NIAR. The 1.0 kg (2.2-lb)
and 1.8 kg (4.0-lb) drone models are also developed in the LS-PrePost using a mass scaling
formulation. The Smooth Particle Hydrodynamics (SPH) technique is used to model the 1.8 kg
bird and verified by simulating its impact on different aluminum plates and comparing the results
with the experimental values. Similarly, the 1.0 kg and 1.2 kg bird models are created using the
verified geometrical relationship. Lastly, a FE model of a single-layer acrylic windshield and
helicopter is generated from the CAD geometry, on which the 1.0 kg SPH bird is numerically
impacted to examine the windshield impact response. The three drone models are impacted
separately on the windshield using LS-DYNA to obtain the safe thickness and the simulation
results and failure damages are compared with the results from the equivalent bird strikes. The
comparative study demonstrates that the damage caused by the drones are different and severer
than that of the bird models. Therefore, this research proposes that hazard severity of UAS should
be considered in the FAA regulations for rotorcraft components airworthiness certifications.
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Thesis (M.S.)-- Wichita State University, College of Engineering, Dept. of Mechanical Engineering
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Wichita State University
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© Copyright 2021 by Yuwaraj Shrestha
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