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Author: search.filters.author.Cortez, Spencer Troy P.Has files: No

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    Four-Bar Path Synthesis for Variable Camber Wing Using Two Steps Approach
    (2026-01-01)
    Cortez, Spencer Troy P.
    ;
    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.
    ;
    Winyangkul, Seksan
    ;
    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.