Proportional fuzzy feed-forward architecture control validation by wind tunnel tests of a morphing wing

Kammegne, Michel Joël Tchatchueng; Botez, Ruxandra Mihaela; Grigorie, Teodor Lucian; Mamou, Mahmoud; Mébarki, Youssef

doi:10.1016/j.cja.2017.02.001

Cited by 27 publications

(7 citation statements)

References 37 publications

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“…In morphing wing analysis regarding design and implementation, (1) analytical or experimental modeling, (2) validation [43,[68][69][70][71], (3) performance and characteristics analysis [72][73][74][75][76][77], and (4) aeroelasticity analysis [78][79][80] are the topics being investigated. Other than those previously mentioned, control systems and flight control and dynamics for morphing wing aircraft [81][82][83] are also seriously studied. In the sense of the technology readiness level (TRL) of morphing aircraft, various levels of analysis and validation have been performed that range from analytical and numerical works to large-scale wind tunnel and flight tests [43,71,84].…”

Section: Introductionmentioning

confidence: 99%

Enhanced Range and Endurance Evaluation of a Camber Morphing Wing Aircraft

Joe

Majid

2023

Biomimetics

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Flight range, endurance, maneuverability, and agility are the key elements that determine an aircraft’s performance. Both conventional and morphing wing aircraft have been well studied and estimated in all aspects of performance. When considering the performance of morphing aircraft, most works address aspects of the aerodynamical performance such as L and D as well as flight envelopes for flight dynamics and control perspectives. However, the actual benefits of adopting morphing technologies in practical aspects such as aircraft operation, mission planning, and sustainability have not been addressed so far. Thus, this paper addresses the practical aspect of the benefits when adopting a camber morphing wing aircraft. Identical geometrical and computational conditions were applied to an already-existing aircraft: the RQ-7a Shadow. The wing structure was switched between a fixed wing and a camber morphing wing to generate conventional and morphing wing geometries. The fixed-wing cases had varying flap deflection angles, and the camber morphing wing cases had varying camber rates from 4% to 8%. Once the CL values of the fixed and morphing wing cases were matched up to two significant figures, the CD and CL/CD were analyzed for these matching cases to calculate the flight endurance, range, and improvement. When NACA 6410 is adopted, a 17% improvement in flight range and endurance average was expected. In the case of NACA 8410, an average 60% improvement was expected.

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Section: Introductionmentioning

confidence: 99%

Enhanced Range and Endurance Evaluation of a Camber Morphing Wing Aircraft

Joe

Majid

2023

Biomimetics

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“…This change can occur in many ways: sweep angle, chord length, span length, and airfoil [1][2][3], as shown in Figure 1. Wing morphing aims to minimize fuel consumption by reducing drag forces in corresponding flight modes [4]. Recently, many researchers have worked towards the study of using smart materials and their aerodynamic reactions to investigate and realize shape morphing [5,6].…”

Section: Introductionmentioning

confidence: 99%

Computational Analysis of 3D Lattice Structures for Skin in Real-Scale Camber Morphing Aircraft

Alsaidi

Joe²,

Akbar

2019

Aerospace

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Conventional or fixed wings require a certain thickness of skin material selection that guarantees structurally reliable strength under expected aerodynamic loadings. However, skin structures of morphing wings need to be flexible as well as stiff enough to deal with multi-axial structural stresses from changed geometry and the coupled aerodynamic loadings. Many works in the design of skin structures for morphing wings take the approach either of only geometric compliance or a simplified model that does not fully represent 3D real-scale wing models. Thus, the main theme of this study is (1) to numerically identify the multi-axial stress, strain, and deformation of skin in a camber morphing wing aircraft under both structure and aerodynamic loadings, and then (2) to show the effectiveness of a direct approach that uses 3D lattice structures for skin. Various lattice structures and their direct 3D wing models have been numerically analyzed for advanced skin design.

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“…This change can occur in many ways: sweep angle, chord length, span length, and airfoil [1][2][3]. Wing morphing mainly aims to minimize fuel consumption by reducing drag forces in corresponding flight modes [4]. Recently, many researchers have moved towards the study of using smart materials and their aerodynamic analysis to investigate shape morphing [5,6].…”

Section: Introductionmentioning

confidence: 99%

Simplified 2D Skin Lattice Models for Multi-Axial Camber Morphing Wing Aircraft

Alsaidi

Joe²,

Akbar

2019

Aerospace

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Conventional fixed wing aircraft require a selection of certain thickness of skin material that guarantees structural strength for aerodynamic loadings in various flight modes. However, skin structures of morphing wings are expected to be flexible as well as stiff to structural and coupled aerodynamic loadings from geometry change. Many works in the design of skin structures for morphing wings consider only geometric compliance. Among many morphing classifications, we consider camber rate change as airfoil morphing that changes its rate of the airfoil that induces warping, twisting, and bending in multi-axial directions, which makes compliant skin design for morphing a challenging task. It is desired to design a 3D skin structure for a morphing wing; however, it is a computationally challenging task in the design stage to optimize the design parameters. Therefore, it is of interest to establish the structure design process in rapid approaches. As a first step, the main theme of this study is to numerically validate and suggest simplified 2D plate models that fully represents multi-axial 3D camber morphing. In addition to that, the authors show the usage of lattice structures for the 2D plate models’ skin that will lead to on-demand design of advanced structure through the modification of selected structure.

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Proportional fuzzy feed-forward architecture control validation by wind tunnel tests of a morphing wing

Cited by 27 publications

References 37 publications

Enhanced Range and Endurance Evaluation of a Camber Morphing Wing Aircraft

Enhanced Range and Endurance Evaluation of a Camber Morphing Wing Aircraft

Computational Analysis of 3D Lattice Structures for Skin in Real-Scale Camber Morphing Aircraft

Simplified 2D Skin Lattice Models for Multi-Axial Camber Morphing Wing Aircraft

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