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This paper attempts to discover the structural behavior of the wing imperiled to flowing loads through the voyage. The study uses a method in the form of finite element analysis of wing flexure distortion. As a first step, two wing models are established by captivating factual features, wing assembly, and plan principles into consideration. The gat...
Citations
... The word "aircraft" refers to an efficient mechanical invention with the ability to fly. The aircraft's two primary parts are its wing and fuselage (Tariq and Mazhar 2021;Elangovan et al. 2019;Bruce 2017;Venkatarthnaiah et al. 2013;Vartabedian 2018;Ajith et al. 2019;Girennavar et al. 2017;Arif 2020;Maheswaran et al. 2015;Madhu and Kadole 2015;Pavan and Manjunath 2018;Zakuan et al. 2019;Fang et al. 2019;Kleemann et al. 2020;Son et al. 2021;Wanhill et al. 1990). The wing of aircraft is made up of numerous airfoils. ...
Background: Study aims to work on the evolution of wing spar in aircraft between 2009 and 2023 using Bibliometric method. Methods: Scopus database was utilized to identify documents related to the keywords “Aircraft,” “Wing,” “Spars,” and “Analysis” from the period of 2009 to 2023. Statistical Analysis was conducted to analyze different types of documents, categorized by source, country, and author. Additionally, the Network analysis was performed using VOS Viewer to explore various aspects such as Co-occurrence, Citation analysis, and Co-authorship. Results: The analysis consists of a total of 345 documents from Scopus containing the specified keywords, covering the time span from 2009 onwards. Within the Engineering domain, approximately 55.2% of the articles were published and United States has the highest contribution in the documents. Conclusion: The statistical analysis reveals the highest document count in 2018 and 2019 for English language, while network analysis emphasizes “Wings” as a crucial keyword in advancing the aerospace industry. Material selection, structural optimisation, fatigue life prediction, and failure analysis were among the topics explored in the investigations. More research into the creation of lightweight and high-strength wing designs helps to improve aircraft performance, safety, and efficiency.
... In 2019 Zakuan et al. [5] used ANSYS software to model the structural behavior of a three-dimensional wing. The deformation of the lifting surface structure has been observed and determined using static structural and modal analysis.in ...
For shorter landing and take-off path in airports, the aircrafts should reduce their speed with keeping high lifting force. This paper is to identify
solutions to increase the lift force of the wing significantly under several flight scenarios (such as takeoff and landing) using leading-edge
slats and their relationship with the dynamic parameters of the aerodynamic wing. The study is performed by the use of ABAQUS 2016
software. The problem is solved for turbulent flow and 2-dimensional composite wing at constant Reynolds’s number of (6.49 × 105) and
constant boundary conditions. Various depths have been used for the auxiliary airfoil at constant width and gap. All stresses at the wing base
were obtained. The pressure distribution on the airfoil surface was determined, air velocity distribution was tracked over the surface, lift and
drag forces and their coefficients were computed. The results show that the highest value of the lift coefficient is 0.489 at the depth (-3 %) of
the wing chord, it decreases when the depth of the slat becomes zero %, and the rise returns with increasing depth to (4 %), but it does not
reach the maximum value, while the highest drag coefficient was (1.89) at depth (4 %) of the wing chord. The maximum value of Von Mises
stress was found at depth of 4 % with value of 1.605 × 105 Pa.
... In 2019 Zakuan et al. [5] used ANSYS software to model the structural behavior of a three-dimensional wing. The deformation of the lifting surface structure has been observed and determined using static structural and modal analysis.in ...
For shorter landing and take-off path in airports, the aircrafts should reduce their speed with keeping high lifting force. This paper is to identify solutions to increase the lift force of the wing significantly under several flight scenarios (such as takeoff and landing) using leading-edge slats and their relationship with the dynamic parameters of the aerodynamic wing. The study is performed by the use of ABAQUS 2016 software. The problem is solved for turbulent flow and 2-dimensional composite wing at constant Reynolds’s number of (6.49 × 105) and constant boundary conditions. Various depths have been used for the auxiliary airfoil at constant width and gap. All stresses at the wing base were obtained. The pressure distribution on the airfoil surface was determined, air velocity distribution was tracked over the surface, lift and drag forces and their coefficients were computed. The results show that the highest value of the lift coefficient is 0.489 at the depth (-3 %) of the wing chord, it decreases when the depth of the slat becomes zero %, and the rise returns with increasing depth to (4 %), but it does not reach the maximum value, while the highest drag coefficient was (1.89) at depth (4 %) of the wing chord. The maximum value of Von Mises stress was found at depth of 4 % with value of 1.605 × 105 Pa.
... Various shapes of the thin-walled structure can be used to suit its application in the mentioned industries. For example, some studies have shown T-shaped thin-walled structures considering various geometries, which are used in aircraft as ribs [2][3][4][5]. Furthermore, Rozylo and Debski [6] experimented on the Z shape of the thin-walled composite structure and showed the enhancement in improving the structural performance of the whole model. ...
In structural engineering, thin-walled structures play an important role in the design of the lightweight structural model. It carries different loading conditions when it exists in any model, and it is designed with thin plates or thin shells. Penetrating thin-walled structures with different kinds of holes can decrease their weight and facilitate repair and maintenance operations, such as those carried out for the wing of an airplane. In such applications, cutouts are often employed as part of the design of composite plates. Therefore, this paper attempted to design and analyse the thin-walled composite structure with a C-cross-section shape. To model and analyse the structures, a finite element method was utilized using the ABAQUS commercial tool, and the results of critical buckling load for different laminate types were obtained. Composite materials and structures have different parameters that can vary the results of analysis; therefore, to optimize the current mode a design of experiments method is used via MINITAB 20 and Design-Expert 13 tools. The selected parameters for this work were the opening ratio, spacing ratio, and shape of the hole for the output response as a critical buckling load was carried out. Based on the current results of simulation and optimization, it was found that the parameters of composite materials and structures will impact the output response, and the current study investigated the optimum parameters for the best possible outcome of the structural analysis.
... Besides, Panettieri et al., [12] applied global/local modelling techniques of structural analysis to optimize structural wing box configuration of the civil aircraft for least weight. Zakuan et al., [13] investigated the static and modal analysis of a three-dimensional wing using ANSYS finite element package. Recently, Basri et al., [14] studied the stress analysis of wing made of NACA4415 under an aerodynamic load generated using Schrenk's approximation. ...
Ribs in aircraft wings maintain the airfoil shape of the wing under aerodynamic loads and also support the resulting bending and shear loads that act on the wing. Aircrafts are designed for least weight and hence the wings are made of hollow torsion box and the ribs are designed with cutouts to reduce the weight of the aircraft structure. These cutouts on the ribs will lead to higher stresses and stress concentration that can lead to failure of the aircraft structures. The stresses depend on the shape of the cutouts in the ribs and thus in the present work, the commercial software ANSYS was used to evaluate the stresses on the ribs with different shapes of cutouts. Four different shapes of cutout were considered to study the effect of cutout shape on the stresses in the ribs. It was found that the best shape for the cutouts on the ribs of wings to reduce weight is elliptical.
... The plane's study includes designing any aircraft components to resist stress from any deformation that occurs. Zakuan et al. [22] investigated the three-dimensional wing's structural behaviour imperiled to flowing loads. For the wing model establishment and the maximum operating Mach number of Airbus A320 is equivalent to 0.82, which is slightly lower operating speeds than its predecessor, A300 and A310. ...
This paper investigates the structural behaviour of the wing subjected to the aerodynamic loads during the flight using finite element analysis of wing flexure deformation. In this work, three different types of wing models are established. Material characteristics, the wing structure, and design principles have been taken into account. The assembly of the wing model consists of the thin skin, two spars, and the multi-ribs. The two spars consist of primary and secondary spars. For this study, NACA 23015 is chosen as the baseline
airfoil as this airfoil is very similar to the customized airfoil being used in Airbus A320. Two spars mainly bear the bending moment and shear force, which are made of titanium alloy to ensure sufficient rigidity. The skin and wing ribs are made of aluminium alloy to lighten the structural weight; a static structural analysis is applied. Total deformation, equivalent elastic strain, and equivalent von Mises stress are obtained to study the wing's structural behaviour. Furthermore, the modal analysis is then applied. The natural frequencies and the modal shape of the wing for three orders are obtained through the pre-stress modal analysis. The modal analysis results help designers minimize excitation on the natural frequencies and prevent the wing from flutter. According to the results, designers can emphasize strengthening and testing the stress concentration and large deformation area.
... Aircraft wings contribute a significant amount to the payload of any aircraft. It consists of many panels, and it is designed simultaneously to achieve an optimum design [1,2]. A good wing design involves the aerodynamic, structural design, as well as material selection [3]. ...
... Muhammad Amir Mirza et al. performed structural analysis over a three-dimensional wing of NACA 23015, which is identical to A320. The paper concludes that a wing with ribs at the root and the tip of the wing shows lesser deformation as compared to a wing that contains spar and wings [2]. ...
... The model in this paper is validated with Zakuan, M.A.M.B.M [2]. For this validation, aluminium alloy is used in the ribs and wing skin, and titanium alloy is used for primary and secondary spars. ...
The use of finite element analysis is increasingly gaining popularity in the design and analysis of aircraft structures. Also, composite materials in the manufacturing and design of aircraft structures are increasing due to their exceptional properties of high stiffness to weight ratio. Applications include Composite structures are made up of laminates with different fibre orientations, which adversely affects the property of the composites formed. For this study, the three main parts of the aircraft wing are considered for designing: the spars, the ribs, and the aircraft’s skin. The spars and made up of aluminium alloy, and the ribs are made up of structural steel. Two different wing models are designed. For Model 1, the skin is assigned Titanium alloy as a material, and for Model 2, CFRP (Carbon Fibre Reinforced Polymer) with resin epoxy is used as the skin material. The ribs are made of structural steel and the spars of titanium alloy for both models. This paper aims to compare the materials mentioned above to find the optimum strength to weight ratio. It was found that, for a given uniform load on the bottom of the aircraft’s skin, a weight reduction of 2.37 % was observed in favour of Model 2, the deformation was reduced by 51 per cent, and the von-Mises stress was reduced by ≈ 85%. This paper’s results can be used in manufacturing structural components of UAV, especially the wings due to lighter weight and more flexibility and durability than standard titanium alloys and the significant role played by the orientation of the plies in deciding the strength of the composite.
... Any failure, eventough small one, in any of these components may bring to a catastrophic condition which lead to disaster causing huge loss of lives and property [2]. The level of failure, especially catastrophe one, of a structural part of an airplane can have disastrous consequence, with may cause in shortening of lifecycle of the airplane [3]. Aircraft wing is very crucial for aircraft operation during its flight cycle started from taxiing, taking off, climbing, cruising, descending, approaching, landing, and then taxiing again. ...
One of the problems in the aviation world is that accidents are increasing. The increase in incidents and accidents can be caused by several factors including human error, weather conditions, and failure of the structure / component of the aircraft. Accidents that occur from failure factors, one of which is caused by cracks that occur in the structure due to continuous loading which does not become more attention until the failure. In this final project an analysis of damage tolerance is carried out at the Wing Centre, Lower Surface and Skin Access Hole locations. The choice of location is because aircraft wings are the most important component in aircraft control while operating. Damage tolerance analysis is carried out as an effort to minimize failures in aircraft structures due to cracks that arise. Damage tolerance analysis is done by giving load in the form of an aircraft wing, then an analysis of the growth of crack length that occurs due to loading. The result of damage tolerance analysis will be obtained crack length, aircraft flight life cycle, and critical crack value. And in this study will also bring up a recommendation that is the right time to do the inspection interval.
... Từ đó cho phép thiết kế hệ thống điều khiển giảm rung động để tránh cấu trúc cánh máy bay biến dạng lớn và hư hỏng. Đây cũng là tiền đề để tiến hành tối ưu hóa về mặt cấu trúc của cánh [7,8,9]. Nghiên cứu phân tích trạng thái động cũng cho phép tìm ra vật liệu làm cánh máy bay phù hợp, đáp ứng về độ bền cánh, giảm tiếng ồn và tránh sự dao động [10,11]. ...
... 9. Chuyển vị uốn theo phương thẳng đứng và biến dạng tương đương khi cộng hưởng theo mode 1 của các mô hình cánh. ...
Bài báo đưa ra tính toán thiết kế kết cấu cho cánh máy bay UAV cỡ nhỏ làm bằng vật liệu composite phục vụ nhiệm vụ quan sát. Thiết kế dựa trên việc phân tích đáp ứng tĩnh và động của kết cấu cánh khi chịu tải khí động bằng phương pháp phần tử hữu hạn và đánh giá khả năng chịu tải của cánh theo tiêu chuẩn phá hủy Tsai-Wu. Ba mô hình cánh khác nhau thỏa mãn yêu cầu về khối lượng thiết kế được xem xét. Dựa trên các phân tích về trường chuyển vị, trường biến dạng và giá trị Tsai-Wu, bài báo đưa ra lựa chọn kết cấu cánh phù hợp
