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New Leading-Edge Reinforcement Design of Aircraft Wing to Withstand Bird Collision
(2026-05-01)
Ngamlikitlert, Suppasin
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Kim, Minsung
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Sleesongsom, Suwin
Bird strikes are a key threat to aircraft wing leading edges. This investigation evaluates a honeycomb block reinforcement concept to improve bird strike resistance while maintaining structural efficiency. A validated simulation was developed using an explicit dynamic finite element approach, in which the bird was modeled as a soft body using smoothed particle hydrodynamics, and the wing leading edge was represented with a honeycomb block reinforcement concept. A design of experiments based on McKay Latin hypercube sampling was applied to comprehensively examine the effects of the geometric parameters on the maximum von Mises stress and maximum deformation. Response surface regression models were then constructed to approximate the impact responses and analyze the model correctness. These models were subsequently integrated into a constrained optimization methodology using sequential quadratic programming and population-based integrated learning to minimize deformation while limiting stress below the material yield threshold. The optimized honeycomb and skin configuration demonstrated a noticeable optimization of the maximum deformation within the yield stress limit compared with the baseline design. The results confirm that the proposed honeycomb block reinforcement concept, combined with a regression-based optimization strategy, constitutes a practical, computationally effective approach to improving bird strike resistance and provides a feasible design option for future impact-resistant wing leading-edge designs.
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Four-Bar Linkage Path Generation Problems Using a New TLBO and Optimum Path Repairing Technique
(2026-03-01)
Winyangkul, Seksan
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Alfouneh, Mahmoud
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Sleesongsom, Suwin
A self-adaptive variant of teaching–learning-based optimization, incorporating a diversity archive and referred to as ATLBO-DA, has been proposed. Combined with a new path repairing technique (PRT), it efficiently accomplishes the four-bar linkage path generation problem, but an upgraded version is needed. An update of ATLBO-DA to self-adaptive teaching–learning-based optimization with evenness factor archive (ATLBO-EFA) and a new path repairing technique are proposed at the present. The diversity archive idea of the original version is replaced with the evenness factor archive to increase the exploitation and exploration performance of the TLBO. An optimum path repairing technique (OPRT) is proposed. This novel approach is used to identify the optimum combination of four-bar mechanism types by employing the concept of Degree of Limiting (DL). Moreover, in this article, a comparative analysis of present update and the previous version use to solve four-bar linkage path generation problems is performed. Several path generation problems are solved using both techniques. The results demonstrate that the updated technique consistently outperforms the earlier version, giving superior values for both mean and minimum descriptive statistics. In addition, the results make it clear that ATLBO-EFA and OPRT are superior to the original version. The result of non-parametric statistic testing using Friedman test indicate that ATLBO-EFA ranks 1st at p-value (0.0455) < α (0.05). It can be concluded that ATLBO-EFA with OPRT offers the best solution for solving the four-bar path synthesis problems.
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Four-Bar Path Synthesis for Variable Camber Wing Using Two Steps Approach
(2026-01-01)
Cortez, Spencer Troy P.
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Sleesongsom, Suwin
The variable camber wing (VCW) mechanism synthesis is a present research aim. The variable camber wing is a main track for development of morphing aircraft from the past to the present due to it seems the high lift device in a traditional modern aircraft, but the separate flow due to its slot can be suppressed with the continuous shape changing. With structural-based camber change, the mechanism design requires a new technique in synthesizing the variable camber mechanism, which expects to adapt its’ trailing edge. The deflection angle causes the VCW to generate an additional lift to the main body wing. The two-step approach is used in designing the new VCW mechanism which is crucial when it starts with aerodynamic analysis at different deflected angles and follow with VCW mechanism synthesis. The mechanism synthesis expects to minimize the error between actual mechanism motion and target trailing edge points. The task of this research is to include design constraints to have the possibility of the four-bar mechanism to work well, and be able to work and be placed inside of the trailing edge. The optimizers are selected to tackle the problem is a variation of teaching learning-based optimization. The results show the proposed method with two-step approach which can synthesize the variable camber wing mechanism and also meet with the design targets.
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The Conceptual Design of a Variable Camber Wing
(2025-06-01)
Cortez, Spencer Troy P.
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Winyangkul, Seksan
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Sleesongsom, Suwin
The variable camber wing (VCW) is a morphing wing design anticipated to enhance unmanned aerial vehicles’ (UAVs’) performance in flight through continuously changing shape. The performance of VCWs has been proven, but techniques for their integration, including aerodynamic analysis, mechanism synthesis, and structural tests, still lag in development at the conceptual design stage. Therefore, this research focuses on designing a variable camber wing, a key area for the advancement of morphing aircraft. Inspired by the high-lift capabilities of traditional aircraft devices but aiming for smoother airflow through continuous shape alteration, this research proposes a novel three-step design for a structurally integrated VCW. This approach begins with a critical aerodynamic analysis to determine wing shape adaptations across various flight conditions, followed by a mechanism synthesis phase to design a four-bar linkage that accurately approximates the desired trailing edge deflections by utilizing a variant of teaching–learning-based optimization. The objective is to minimize error between the intended and actual coupler link while adhering to design constraints for proper integration in the wing structure. Finally, structural analysis evaluates the skin’s ability to withstand operational loads and ensure the integrity of the VCW system. The design result demonstrates the success of this three-step approach to synthesizing a VCW mechanism that meets the defined aerodynamic (actual deflection of 9.1764°) and structural targets (maximum Von Mises stress of 81.5 MPa and maximum deflection of 0.073 m), paving the way for enhanced aircraft performance.
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Aircraft Wing Design Against Bird Strike Using Metaheuristics
(2025-05-01)
Timhede, Vanessa
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Timhede, Silvia
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Winyangkul, Seksan
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Sleesongsom, Suwin
Bird strikes pose a significant threat to aviation safety, particularly affecting the wing structures of aircraft. This research aims to design and analyze the impact of bird strikes on wing structures using response surface method and metaheuristics (MHs), which are used to explore various risk minimization and damage mitigation techniques. The optimization problem is the minimization of the maximum von Mises stress of aircraft wing structure against bird strike that is subject to displacement and stress constraints. The design variables include skin and rib thickness, as well as sweep angle. Difficulty due to embedded bird strike simulation and optimization design can be alleviated using a response surface method (RSM). The regression technique in the RSM of the data can reach our goal of model fitting with a higher R<sup>2</sup> until 0.9951 and 0.9919 are obtained for the displacement and von Mises stress model, respectively. The response surface function of the displacement and von Mises stress are related to skin thickness, while sweep angles rather than rib thickness have a greater impact on both design variables. The optimized design of the design variables is performed using MHs, which are TLBO, JADE, and PBIL. The comparative result of MHs can conclude that the PBIL outperformed others in all descriptive statistics. The optimized design results revealed that the optimum solution can release better energy due to bird strike with the highest limit of skin thickness, moderate rib thickness, and less than half of the sweep angle. The results are in accordance with the response surface function analysis. In conclusion, the optimized design of the aircraft wing structure against bird strike can be accomplished with our proposed technique.
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A New Conceptual Design of Twisting Morphing Wing
(2025-02-01)
Kumkam, Noppawit
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Suratemeekul, Napat
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Sleesongsom, Suwin
This research aims to enhance the performance of unmanned aerial vehicles (UAVs) by investigating the impact of twisting wingtip (TWT) on UAVs’ wing aeroelastic and structural behavior using MATLAB and ANSYS simulations. The study focuses on a simplified twisting wingtip design and its aeroelastic effect. This study includes both static and dynamic aeroelastic phenomena. Previous research has primarily focused on only flutter speed while neglecting divergence speed and lift-effectiveness in design results. Numerical and experimental validation underscores the model’s fidelity and its practical applicability. The TWT is designed to exhibit a predominant torsional mode using a guide mode preference technique. The design results reveal that the twist morphing wing improves structural and aeroelastic performance due to its unique twisting deformation capabilities. Furthermore, this research contributes fundamental insights into a specific twist morphing wing concept, highlighting its potential to enhance UAV performance through twisting wingtip technologies. The torsional mode can be predetermined using the guide mode preference technique. Notably, the divergence speed analysis confirms that the twisting shaft position should not exceed the aerodynamic center, which is located at 0.2103 of the chord length. This serves as the theoretical foundation for the TWT design in this study. The adjustment of the TWT’s twisting angle is confirmed to provide optimal divergence speed improvement within a range of 0% to 27.7%. Additionally, the relative aeroelastic efficiencies indicate that the highest lift effectiveness is 0.68% at a twisting angle of 30°, following an exponential relationship, which can be further extended to aircraft control laws. However, the relative efficiency of flutter speed is not significantly improved by the TWT, showing only a marginal improvement of 0% to 1.84% when twisting up and down, in accordance with previous research findings.
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A New Latin Hypercube Sampling with Maximum Diversity Factor for Reliability-Based Design Optimization of HLM
(2024-07-01)
Phromphan, Pakin
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Suvisuthikasame, Jirachot
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Kaewmongkol, Metas
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Chanpichitwanich, Woravech
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Sleesongsom, Suwin
This research paper presents a new Latin hypercube sampling method, aimed at enhancing its performance in quantifying uncertainty and reducing computation time. The new Latin hypercube sampling (LHS) method serves as a tool in reliability-based design optimization (RBDO). The quantification technique is termed LHSMDF (LHS with maximum diversity factor). The quantification techniques, such as Latin hypercube sampling (LHS), optimum Latin hypercube sampling (OLHS), and Latin hypercube sampling with maximum diversity factor (LHSMDF), are tested against mechanical components, including a circular shaft housing, a connecting rod, and a cantilever beam, to evaluate its comparative performance. Subsequently, the new method is employed as the basis of RBDO in the synthesis of a six-bar high-lift mechanism (HLM) example to enhance the reliability of the resulting mechanism compared to Monte Carlo simulation (MCS). The design problem of this mechanism is classified as a motion generation problem, incorporating angle and position of the flap as an objective function. The six-bar linkage is first adapted to be a high-lift mechanism (HLM), which is a symmetrical device of the aircraft. Furthermore, a deterministic design, without consideration of uncertainty, may lead to unacceptable performance during the manufacturing step due to link length tolerances. The techniques are combined with an efficient metaheuristic known as teaching–learning-based optimization with a diversity archive (ATLBO-DA) to identify a reliable HLM. Performance testing of the new LHSMDF reveals that it outperforms the original LHS and OLHS. The HLM problem test results demonstrate that achieving optimum HLM with high reliability necessitates precision without sacrificing accuracy in the manufacturing process. Moreover, it is suggested that the six-bar HLM could emerge as a viable option for developing a new high-lift device in aircraft mechanisms for the future.
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Reliability-Based Topology Optimization with a Proportional Topology for Reliability
(2024-06-01)
Kumkam, Noppawit
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Sleesongsom, Suwin
This research proposes an efficient technique for reliability-based topology optimization (RBTO), which deals with uncertainty and employs proportional topology optimization (PTO) to achieve the optimal reliability structure. The recent technique, called proportional topology optimization for reliability (PTOr), uses Latin hypercube sampling (LHS) for uncertainty quantification. The difficulty of the double-loop nested problem in uncertainty quantification (UQ) with LHS can be alleviated by the power of PTO, enabling RBTO to be performed easily. The rigorous advantage of PTOr is its ability to accomplish topology optimization (TO) without gradient information, making it faster than TO with evolutionary algorithms. Particularly, for reliability-based topology design, evolutionary techniques often fail to achieve satisfactory results compared to gradient-based techniques. Unlike recent PTOr advancement, which enhances the RBTO performance, this achievement was previously unattainable. Test problems, including an aircraft pylon, reveal its performances. Furthermore, the proposed efficient framework facilitates easy integration with other uncertainty quantification techniques, increasing its performance in uncertainty quantification. Lastly, this research provides computer programs for the newcomer studying cutting-edge knowledge in engineering design, including UQ, TO, and RBTO, in a simple manner.
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High-lift mechanism synthesis using an unconventional technique
(2024-05-17)
Satayanusakkul, Kittipong
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Wantapocathum, Tanachot
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Phavichitr, Supanut
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Sleesongsom, Suwin
This research has two aims, a high-lift mechanism (HLM) synthesis using an unconventional technique and reliability-based design optimization (RBDO). The HLM is an important mechanism to control a lifting surface (flap) to generate addition lift during take-off and landing of an aircraft. The mechanism can work well with high precision, increasing performance of the flap. The HLM is one kind of four-bar mechanism, which is still used in commercial aircraft from Airbus and Boeing. The difficulty in design is to suppress the error of the actual motion and its targets. In previous studies, there are only two target points that included positions and angles of flaps during take-off and landing. This kind of the problem is called a motion generation problem. An inherent characteristic of this mechanism is that the design can meet all targets, but not for over nine points. The performance of the mechanism depends on the design technique and number of target points. Unconventional techniques for generating path and additional points as well as reliability-based design is proposed to increase HLM performance. The objective functions are to minimize the position and angle of the flaps, while design constraints include Grashof's law and working space. In a reliability-based design optimization problem, uncertainty due to link length tolerance is included in this problem to make it more reliable. Teaching-learning based optimization with a diversity archive (ATLBO-DA) is used as an optimizer in this study. The results reveal the proposed technique can be used to synthesize an HLM for greater reliability.
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Uncertainty Quantification Code Written in MATLAB
(2024-01-01)
Suratemeekul, Napat
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Kumkam, Noppawit
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Sleesongsom, Suwin
This research presents examples of MATLAB code for a classroom of uncertainty quantification. The codes are developed for educational purposes and newcomers or researchers. Demonstration codes are presented in form of a general design conditions. Examples are chosen from mechanical components, which are simply understood. The mechanical components are shafts, connecting rod, rear shaft housing, and bolt etc. The quantification techniques are in the group of probabilistic such as Monte Carlo Simulation (MCS) and Latin Hypercube Sampling (LHS). These examples can help the newcomers to understand the difficulty in uncertainty quantify and extend to calculate reliability value and probability of failure. Example computer codes are included in all parts.

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