PSI - Issue 14

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedirect.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 14 (2019) 416–428 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000–000

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2nd International Conference on Structural Integrity and Exhibition 2018 Bird strike damage and analysis of UAV’s airframe 2nd International Conference on Structural Integrity and Exhibition 2018 Bird strike damage and analysis of UAV’s airframe

XV Portuguese Conference on Fracture, PCF 2016, 10-12 February 2016, Paço de Arcos, Portugal Thermo-mechanical modeling of a high pressure turbine blade of an airplane gas turbine engine P. Brandão a , V. Infante b , A.M. Deus c * a Department of Mechanical Engineering, Instituto Superior Técnico, Universidade de Lisboa, Av. Rovisco Pais, 1, 1049-001 Lisboa, Portugal b IDMEC, Department of Mechanical Engineering, Instituto Superior Técnico, Universidade de Lisboa, Av. Rovisco Pais, 1, 1049-001 Lisboa, Portugal c CeFEMA, Department of Mechanical Engineering, Instituto Superior Técnico, Universidade de Lisboa, Av. Rovisco Pais, 1, 1049-001 Lisboa, Portugal Abstract During their operation, modern aircraft engine components are subjected to increasingly demanding operating conditions, especially the high pressure turbine (HPT) blades. Such conditions cause these parts to undergo different types of time-dependent degradation, one of which is creep. A model using the finite element method (FEM) was developed, in order to be able to predict the creep behaviour of HPT blades. Flight data records (FDR) for a specific aircraft, provided by a commercial aviation company, were used to obtain thermal and mechanical data for three different flight cycles. In order to create the 3D model needed for the FEM analysis, a HPT blade scrap was scanned, and its chemical composition and material properties were obtained. The data that was gathered was fed into the FEM model and different simulations were run, first with a simplified 3D rectangular block shape, in order to better establish the model, and then with the real 3D mesh obtained from the blade scrap. The overall expected behaviour in terms of displacement was observed, in particular at the trailing edge of the blade. Therefore such a model can be useful in the goal of predicting turbine blade life, given a set of FDR data. © 2019 The Auth rs. Published by Elsevier B.V. This is an o en access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and pe r-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. Akhilesh Kumar Jha a *, S Sathyamoorthy a , Viswa Prakash a a Aeronautical Development Establishment, DRDO, New Thippasandra Road, Bengaluru 560075, India Abstract Composite materials are increasingly being used for Aircraft/UAVs structures such as wing components or fuselage panels, etc. A collision to bird during flight can lead to serious damage to the Aircraft/UAVs structures, particularly during takeoff and landing phases. The Federal Aviation Regulations (FAR) requires that all forward facing components need to prove a certain level of bird strike resistanc in certification tests before they are all wed for operational use. This paper focuses on the numerical modeling and simulation of a two-pound bird impact on composite structures of the UAV using ABAQUS/Explicit with impact velocities ranging from 40m/s and 60m/s. The bird is modeled using Coupled Eulerian Lagrangian (CEL) technique using a material model with properties similar to fluid. The internal pressure of the bird model is linked to the change in volume with an Equation of State (EOS). Based on simulation results, the high probability strike zone has been reinforced and fifteen successful flights have been achieved. The experimental tests will be carried out on panel level, taken from various airframes modules of the UAV. © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. Keywords: Composite; UAV; ABAQUS/Explicit; CEL; EOS 1. Introduction An unmanned aerial vehicle (UAV), commonly known as a drone, is an aircraft without a human pilot aboard. The flight of UAVs may operate with various degrees of autonomy: either under remote control by a human operator, or Akhilesh Kumar Jha a *, S Sathyamoorthy a , Viswa Prakash a a Aeronautical Development Establishment, DRDO, New Thippasandra Road, Bengaluru 560075, India Abstract Comp site materials are increasi gly being used for Aircraft/UAVs structures uch as wing components or fuselage panels, etc. A collision to bird during flight can lead to serious damage to the Aircraft/UAVs structures, particularly during takeoff and landing phas s. The Federal Aviation Regulations (FAR) requires that all forw rd f cing components need to prove a certain level of bird strike resis ance in certification tests before they are allowed for operational use. This paper focuses on the numerical modeling and simulation of a two-pound bird impact on compo te structures of the UAV using ABAQUS/Explicit with imp ct velociti s ranging from 40m/s nd 60m/s. he bird is modeled using Coupled Eulerian Lagrangian (CEL) technique using a m erial model with properties similar to fluid. The int rnal pressure of the bird model i linked to the change in volume with an Equation of State (EOS). Based on simulation results, th high pr bability strik zone has been reinforced and fifteen successful flights have been achieved. T e experimental tests will be carried out on panel level, taken from various airframes modules of the UAV. © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by- c-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. Keywords: Composite; UAV; ABAQUS/Explicit; CEL; EOS 1. Introduction An unmanne aerial vehicle (UAV), commonly known as a drone, is an aircraft without a human pilot aboard. The flight of UAVs may operate with various degrees of autonomy: either under remote control by a human operator, or © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016.

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation.

* Corresponding author. Tel.:+91-080-2505-7118; fax: +91-080-2505-7227. E-mail address: akhileshjha@ade.drdo.in * Correspon ing aut or. Tel.:+91-080-2505-7118; fax: +91-080-2505-7227. E-mail address: akhileshjha@ade.drdo.in

2452-3216 © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. 2452-3216 © 2018 The Authors. Published by Elsevier B.V. This is a open access article und r the CC BY-NC-ND lic nse (https://creat vecommons.org/licenses/by- c-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers.

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 2452-3216  2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. 10.1016/j.prostr.2019.05.051