A Review on Evolution of Aeroelastic Assisted Wing

Sivanandi, Periyasamy; Gupta, Chirag; Durai, Hari

doi:10.1007/s42405-023-00583-7

Cited by 10 publications

(3 citation statements)

References 150 publications

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“…The field of aircraft design and aerospace engineering has continually sought new technologies and innovations to enhance flight performance, versatility, and efficiency. In this ever-evolving domain, morphing wing technologies (Li et al, 2018;Majid et al, 2021;Sivanandi et al, 2023) have played a pivotal role, given their potential significant advantages and adaptability in catering to diverse flight missions. Among these technologies, the variable trailing edge cambered wing has garnered substantial interest due to its capability to allow real-time adjustments in the wing's trailing edge during flight, thus optimizing flight performance (Schlup et al, 2021;Bishay et al, 2022).…”

Section: Introductionmentioning

confidence: 99%

Honeycomb structure filling morphing wing trailing edge: Design strategy, deformation feedback, and active control

Li,

Sun,

Pan

et al. 2024

Program. mater.

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Pursuing highly efficient aerodynamic efficiency in aircraft has driven the development of morphing wing technology. However, there are still limitations to morphing wing technology, including adaptation of load and deformation, and deformation monitoring and control. This work introduces an intelligent trailing edge structure that balances deformation and load-bearing and achieves deformation monitoring and active control. Firstly, we employ a honeycomb structure for non-uniform filling of the trailing edge. The filling method is obtained through inverse design using a genetic algorithm based on neural networks, allowing the device to undergo continuous deformation while meeting load-bearing requirements. The bending deformation of the wing is achieved using shape memory alloy (SMA) wire. Additionally, we design and fabricate a metal-based multichannel flexible sensor, and based on beam bending theory, we establish the strain–displacement relationship. These sensors are affixed to the trailing edge surface, enabling real-time monitoring and active control of trailing edge deformation. Building an experimental platform to test this system, the results show that the sensors can accurately give feedback on the degree of wing deformation, and the error of active deformation control technology is less than 4%. This provides a new method for the deformation feedback control closed-loop system of intelligent variant wings.

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Section: Introductionmentioning

confidence: 99%

Honeycomb structure filling morphing wing trailing edge: Design strategy, deformation feedback, and active control

Li,

Sun,

Pan

et al. 2024

Program. mater.

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“…Traditional methods for measuring deformation, such as the use of strain gauges [4] and linear variable differential transformers (LVDTs) [5], face limitations in high-temperature environments [6]. Recently, the application of digital image correlation (DIC) systems for deformation measurement [7,8] in high-temperature conditions has gained increasing prominence among researchers [9][10][11][12][13][14][15]. DIC provides several advantages, including full-field measurements for capturing comprehensive deformation data, insensitivity to vibration to minimize external interference, the ability to measure large strain and significant rigid body motion, and adaptability to various specimen shapes.…”

Section: Introductionmentioning

confidence: 99%

High-Temperature DIC Deformation Measurement under High-Intensity Blackbody Radiation

Han,

Goo

2024

Aerospace

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During the high-speed flight of a vehicle in the atmosphere, surface friction with the air generates aerodynamic heating. The aerodynamic heating phenomenon can create extremely high temperatures near the surface. These high temperatures impact material properties and the structure of the aircraft, so thermal deformation measurement is essential in aerospace engineering. This paper revisits high-temperature deformation measurement using the digital image correlation (DIC) technique under high-intensity blackbody radiation with a precise speckle pattern fabrication and a heat haze reduction method. The effects of the speckle pattern on the DIC measurement have been thoroughly studied at room temperature, but high-temperature measurement studies have not reported such effects so far. We found that the commonly used methods to reduce the heat haze effect could produce incorrect results. Hence, we propose a new method to mitigate heat haze effects. An infrared radiation heater was employed to make an experimental setup that could heat a specimen up to 950 °C. First, we mitigated image saturation using a short-wavelength bandpass filter with blue light illumination, a standard procedure for high-temperature DIC deformation measurement. Second, we studied how to determine the proper size of the speckle pattern in a high-temperature environment. Third, we devised a reduction method for the heat haze effect. As proof of the effectiveness of our developed experimental method, we successfully measured the deformation of stainless steel 304 specimens from 25 °C to 800 °C. The results confirmed that this method can be applied to the research and development of thermal protection systems in the aerospace field.

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“…Investigations on aeroelastic wings have attracted the attention of many researchers in recent years [3]. According to [4], the aeroelastic phenomena in the wings can interfere with the design and performance of the aircraft [4].…”

Section: Introductionmentioning

confidence: 99%

Characterization of Aeroelastic Behavior in a High Aspect Ratio Wing Using Computational and Wind Tunnel Experiments

Westin,

Balthazar,

da Silva

et al. 2023

Axioms

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The objective of this article is to characterize an aeroelastic system in terms of its dynamical behavior, which could be either chaotic or periodic before, during, and after achieving the flutter velocity. The aeroelastic system shown here is a wing with a high aspect ratio, which leads to a very flexible behavior subjected to unsteady flow. This paper compares the computational and experimental dynamical behavior of an aeroelastic system at the flutter velocity for the different dynamic stall models proposed. To understand the nonlinear behavior of this system, the traditional attractor reconstruction and Lyapunov exponent calculation are compared with the 0–1 test. In addition to this comparison, two dynamic stall semi-empirical models are applied directly to the time history. All these comparisons show that the computational and wind tunnel experiments are in good agreement, and the dynamic behavior usually gives close results for the 0–1 test and Lyapunov exponent. It is concluded that the system presents chaotic behavior when no dynamic stall correction is applied or when Gangwani’s correction is applied. However, Boeing–Vertol’s correction postpones the chaotic behavior, meaning that the chaotic behavior is only observed for velocities above the flutter.

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A Review on Evolution of Aeroelastic Assisted Wing

Cited by 10 publications

References 150 publications

Honeycomb structure filling morphing wing trailing edge: Design strategy, deformation feedback, and active control

Honeycomb structure filling morphing wing trailing edge: Design strategy, deformation feedback, and active control

High-Temperature DIC Deformation Measurement under High-Intensity Blackbody Radiation

Characterization of Aeroelastic Behavior in a High Aspect Ratio Wing Using Computational and Wind Tunnel Experiments

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