scholarly journals Numerical research on the effect of aircraft leading-edge curvature on bird strike resistance

2021 ◽  
Vol 1798 (1) ◽  
pp. 012044
Author(s):  
K Su ◽  
R X Bai ◽  
H S Bai
Keyword(s):  
Leading Edge ◽  
Bird Strike ◽  
Numerical Research

scholarly journals Analysis and Design of a Leading Edge with Morphing Capabilities for the Wing of a Regional Aircraft—Gapless Chord- and Camber-Increase for High-Lift Performance

2021 ◽  
Vol 11 (6) ◽  
pp. 2752
Author(s):  
Conchin Contell Asins ◽  
Volker Landersheim ◽  
Dominik Laveuve ◽  
Seiji Adachi ◽  
Michael May ◽  
...  
Keyword(s):  
Leading Edge ◽  
Bird Strike ◽  
High Lift ◽  
Analysis And Design ◽  
Actuation System ◽  
Aerodynamic Properties ◽  
Reinforced Plastic ◽  
Stall Angle ◽  
Carbon Fibre Reinforced Plastic ◽  
Electromechanical Actuation

In order to contribute to achieving noise and emission reduction goals, Fraunhofer and Airbus deal with the development of a morphing leading edge (MLE) as a high lift device for aircraft. Within the European research program “Clean Sky 2”, a morphing leading edge with gapless chord- and camber-increase for high-lift performance was developed. The MLE is able to morph into two different aerofoils—one for cruise and one for take-off/landing, the latter increasing lift and stall angle over the former. The shape flexibility is realised by a carbon fibre reinforced plastic (CFRP) skin optimised for bending and a sliding contact at the bottom. The material is selected in terms of type, thickness, and lay-up including ply-wise fibre orientation based on numerical simulation and material tests. The MLE is driven by an internal electromechanical actuation system. Load introduction into the skin is realised by span-wise stringers, which require specific stiffness and thermal expansion properties for this task. To avoid the penetration of a bird into the front spar of the wing in case of bird strike, a bird strike protection structure is proposed and analysed. In this paper, the designed MLE including aerodynamic properties, composite skin structure, actuation system, and bird strike behaviour is described and analysed.

Analysis of High Velocity Impact on Composite Structures

2014 ◽  
Vol 617 ◽  
pp. 104-109 ◽  
Author(s):  
Milan Žmindák ◽  
Zoran Pelagić ◽  
Maroš Bvoc
Keyword(s):  
Carbon Fibers ◽  
Composite Structures ◽  
Impact Resistance ◽  
Leading Edge ◽  
Layered Composite ◽  
Bird Strike ◽  
Out Of Plane ◽  
The Matrix ◽  
Composite Wing ◽  
Considerable Damage

In the recent years a big focus is subjected to the response of structures subjected to out-of-plane loading such as blasts, impact, etc. not only to homogenous materials, but also to heterogeneous materials, such as composites. Such form of loading can cause considerable damage to the structure. In the case of layered composite materials the damage can have several forms, starting from damage in layers up to delamination and full damage of the construction. This paper describes the investigation of shockwave propagation in composite structures caused by impact loading. The composite consists of carbon fibers in a polymer matrix, in which the fibers are much stiffer then the matrix. Finite element simulations were carried out for a “bird” strike impact on a composite wing leading edge. Results show a good impact resistance and good damping abilities of shockwaves.

scholarly journals Effect of bird-strike on sandwich composite aircraft wing leading edge

2020 ◽  
Vol 148 ◽  
pp. 102839 ◽  
Author(s):  
B. Arachchige ◽  
H. Ghasemnejad ◽  
M. Yasaee
Keyword(s):  
Leading Edge ◽  
Sandwich Composite ◽  
Bird Strike ◽  
Aircraft Wing

Review of current research trends in bird strike and hail impact simulations on wing leading edge

2018 ◽  
Vol 90 (4) ◽  
pp. 602-612 ◽  
Author(s):  
Zdobyslaw Jan Goraj ◽  
Kamila Kustron
Keyword(s):  
Computer Simulations ◽  
Leading Edge ◽  
Simulation Models ◽  
Bird Strike ◽  
Physical Test ◽  
Content Type ◽  
Physical Tests ◽  
Statistical Approaches ◽  
The Impact ◽  
Hail Impact

Purpose Bird strike and hail impact resistances are considered in relation to the fulfilment of airworthiness/crashworthiness regulations as specified by appropriate aviation authorities. Before aircraft are allowed to go into service, these regulations must be fulfilled. This includes the adaption of the wing leading edge (LE) structure to smart diagnostics and an easy repair. This paper aims to focus on the wing LE, although all forward-facing aircraft components are exposed to the impact of foreign object during the flight. The best practices based on credible simulations which may be appropriate means of establishing compliance with European Aviation safety Agency and Federal Aviation Administration regulations regarding bird strikes, together with the problem of collisions with hailstones, are overviewed in aspect of accuracy and computing cost. Design/methodology/approach The best means of evaluating worldwide certification standards so as to be more efficient for all stakeholders by reducing risk and costs (time and money consuming) of certification process are recommended. The very expensive physical tests may be replaced by adequate and credible computer simulations. The adequate credible simulation must be verified and validated. The statistical approaches for modelling the uncertainty are presented in aspect of computing cost. Findings The simulation models have simplifications and assumptions that generate an uncertainty. The uncertainty must be identified in benchmarking tests. Instead of using “in house” physical tests, there are scientific papers available in open literature thanks to the new trend in worldwide publication of the research results. These large databases can be efficiently transform into useful benchmark thanks to data mining and knowledge discovery methods and big data analyses. The physical test data are obtained from tests on the ground-based demonstrator by using high-speed cameras and a structural health monitoring system, and therefore, they should be applied at an early stage of the design process. Originality/value The sources of uncertainty in simulation models are expressed, and the way to their assessment is presented based on statistical approaches. A brief review of the current research shows that it widely uses efficient numerical analysis and computer simulations and is based on finite element methods, mesh structure as well as mesh free particle models. These methods and models are useful to analyse airworthiness requirements for damage tolerance regarding bird-strike and hail impact and haves been subjected to critical review in this paper. Many original papers were considered in this analysis, and some of them have been critically reviewed and commented upon.

Dynamic response of bird strike on honeycomb-based sandwich panels of composite leading edge

2020 ◽  
pp. 1-14
Author(s):  
Ju Qiu ◽  
Dong Wang ◽  
Chuanjun Liu ◽  
Lin Chen ◽  
Hailong Huang ◽  
...  
Keyword(s):  
Dynamic Response ◽  
Sandwich Panels ◽  
Leading Edge ◽  
Bird Strike

A novel design for reinforcing the aircraft tail leading edge structure against bird strike

2017 ◽  
Vol 105 ◽  
pp. 89-101 ◽  
Author(s):  
Jun Liu ◽  
Yulong Li ◽  
Xiancheng Yu ◽  
Zhongbin Tang ◽  
Xiaosheng Gao ◽  
...  
Keyword(s):  
Leading Edge ◽  
Bird Strike ◽  
Edge Structure ◽  
Novel Design

Efficiency Metallic Leading Edge Structure Bird Strike Resistant Design

2011 ◽  
Vol 338 ◽  
pp. 84-89 ◽  
Author(s):  
Mei Ying Zhao ◽  
Jing Jing Li
Keyword(s):  
Numerical Simulation ◽  
Absorption Rate ◽  
Leading Edge ◽  
Experimental Results ◽  
Structural Quality ◽  
Bird Strike ◽  
Edge Structure ◽  
Simulation Based ◽  
Simulation Results ◽  
Resistant Structure

This article investigated a new metallic leading edge bird strike resistant structure, using corrugate board as its enhanced component to absorb more bird kinetic energy. This structure was called as Corrugate Board Leading Edge (CBLE) structure. To verify the structure’s bird strike resistant ability, numerical simulation based on the LS-DYNA was carried out, and succeeding experiments were performed. However, the experimental results were not exciting. They were not as the simulation results we expected. The reasons were analyzed through this article. Finally a rivet-relative model was created considering the influence of riveting. This model was proved to be accurate by comparing with experimental results. Based on the analysis above, an Optimized CBLE (O-CBLE) structure was used to optimize the bird strike resistant ability, the energy absorption rate of O-CBLE structure increased 11.4% while the structural quality was only slightly increased.

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