Aerospace

22 pages, 14228 KiB

Open AccessArticle

Flow Field Reconstruction of 2D Hypersonic Inlets Based on a Variational Autoencoder

by Zuwei Tan, Runze Li and Yufei Zhang

Aerospace 2023, 10(9), 825; https://doi.org/10.3390/aerospace10090825 - 21 Sep 2023

Cited by 1 | Viewed by 1581

The inlet is one of the most important components of a hypersonic vehicle. The design and optimization of the hypersonic inlet is of great significance to the research and development of hypersonic vehicles. In recent years, artificial intelligence techniques have been used to [...] Read more.

The inlet is one of the most important components of a hypersonic vehicle. The design and optimization of the hypersonic inlet is of great significance to the research and development of hypersonic vehicles. In recent years, artificial intelligence techniques have been used to improve the efficiency of aerodynamic optimization. Deep generative models, such as variational autoencoder (VAE) and generative adversarial network (GAN), have been used in a variety of flow problems in the last two years, making fast reconstruction and prediction of the full flow field possible. In this study, a hybrid multilayer perceptron (MLP) combined with a VAE network is used to reconstruct and predict the flow field of a two-dimensional multiwedge hypersonic inlet. The obtained results show that the VAE network can reconstruct the overall flow structure of the hypersonic flow field with high accuracy. The reconstruction accuracy of complex flow structures, such as shockwaves, boundary layers, and separation bubbles, is satisfactory. The flow field prediction model based on the MLP-VAE hybrid model has a strong generalization and generation ability, achieving relatively accurate flow field prediction for inlets with geometric configurations outside the training set. Full article

(This article belongs to the Special Issue Aerodynamic Design with Machine Learning)

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20 pages, 35978 KiB

Open AccessArticle

Investigation of the Influence of Wake Field Characteristic Structures on Downstream Targets Using the POD Method

by Jiawei Fu, Junhui Wang, Jifei Wu, Ke Xu and Shuling Tian

Aerospace 2023, 10(9), 824; https://doi.org/10.3390/aerospace10090824 - 21 Sep 2023

Viewed by 1204

Abstract

This research investigated the impact of complex low-speed wake flow structures on the aerodynamic characteristics of objects downstream. It employed the proper orthogonal decomposition (POD) method and the domain precursor simulation method to compare traditional methods and validate this approach. The study generated [...] Read more.

This research investigated the impact of complex low-speed wake flow structures on the aerodynamic characteristics of objects downstream. It employed the proper orthogonal decomposition (POD) method and the domain precursor simulation method to compare traditional methods and validate this approach. The study generated several flow structures of parallel dual-cylinder wakes with different scales and spacing. The variations in the aerodynamic coefficient of three downstream objects at various times passing through wakes of varying scales were appropriately compared and analyzed. The study established that the wake with a cylinder spacing of G = 1.5 has a more compact and concentrated modal structure than that with a cylinder spacing of G = 0.35. Smaller objects were more responsive to the wake flow structure with a spacing of G = 1.5, whereas larger objects responded more to the flow structure with a spacing of G = 0.35. The achieved results also revealed that the aerodynamic force coefficients of objects passing through the wakefield at different times were closely related to the temporal characteristics of the wake flow structure with different scales. Full article

(This article belongs to the Special Issue Vortex Flow Phenomena and Physics of Aerospace Engineering Applications)

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21 pages, 7447 KiB

Open AccessArticle

Very High Cycle Fatigue Life Prediction of SLM AlSi10Mg Based on CDM and SVR Models

by Yibing Yu, Linlin Sun, Zhi Bian, Xiaojia Wang, Zhe Zhang, Chao Song, Weiping Hu and Xiao Chen

Aerospace 2023, 10(9), 823; https://doi.org/10.3390/aerospace10090823 - 21 Sep 2023

Cited by 2 | Viewed by 1547

Abstract

A novel fatigue evolution model considering the effect of defect size and additive manufacturing building direction based on the theories of continuum damage mechanics and its numerical implementation in ABAQUS is proposed in this paper. First, the constitutive model, fatigue damage evolution model [...] Read more.

A novel fatigue evolution model considering the effect of defect size and additive manufacturing building direction based on the theories of continuum damage mechanics and its numerical implementation in ABAQUS is proposed in this paper. First, the constitutive model, fatigue damage evolution model and their parameter calibration methods are presented. Second, using the ABAQUS platform, the proposed model is implemented with user-defined subroutines. After that, based on the proposed model and its numerical implementation, the fatigue life of additively manufactured AlSi10Mg is predicted and its applicability is verified through experimental results. Finally, a support vector regression model is established to predict the fatigue life, and its results are compared to those of the numerical finite element method. The results show that the support vector regression model makes better predictions than the finite element method. Full article

(This article belongs to the Special Issue Computing Methods for Aerospace Reliability Engineering)

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10 pages, 1118 KiB

Open AccessArticle

Trend Analysis of Civil Aviation Incidents Based on Causal Inference and Statistical Inference

by Peng He and Ruishan Sun

Aerospace 2023, 10(9), 822; https://doi.org/10.3390/aerospace10090822 - 21 Sep 2023

Cited by 1 | Viewed by 1935

Abstract

The efficient management of aviation safety requires the precise analysis of trends in incidents. While classical statistical models often rely on the autocorrelation of indicator sequences for trend fitting, significant room remains for performance improvement. To enhance the accuracy and interpretability of trend [...] Read more.

The efficient management of aviation safety requires the precise analysis of trends in incidents. While classical statistical models often rely on the autocorrelation of indicator sequences for trend fitting, significant room remains for performance improvement. To enhance the accuracy and interpretability of trend analyses for aviation incidents, we propose the Causal-ARIMA model, which is grounded in causal inference theory, and we employ four distinct modeling strategies to fit the trend of incidents in China’s civil aviation sector between 1994 and 2020. The objective is to validate the performance of the Causal-ARIMA model and identify optimal trend analysis strategies. The four modeling strategies account for causation factors, stationarity, and causality with operational volume, incorporating models like AR, ARMA, ARIMA, and Causal-ARIMA. Our findings reveal that ensemble techniques incorporating the Causal-ARIMA model (Strategy 2 and 3) outperform classical trend analysis methods (Strategy 1) in terms of model fit. Specifically, the causality-based binary fitting technique (Strategy 3) achieves the most uniformly dispersed fitting performance. When the premises for using the Causal-ARIMA model are relaxed, applying it to variables without Granger causal relationships results in uneven model performance (Strategy 4). According to our study, the Causal-ARIMA model can serve as a potent tool for the analysis of trends in the domain of aviation safety. Modeling strategies based on the Causal-ARIMA model provide valuable insights for aviation safety management. Full article

(This article belongs to the Special Issue Civil and Military Airworthiness: Recent Developments and Challenges (Volume III))

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19 pages, 8705 KiB

Open AccessArticle

Dynamic Analysis of a Large Deployable Space Truss Structure Considering Semi-Rigid Joints

by Huaibo Yao, Yixin Huang, Wenlai Ma, Lei Liang and Yang Zhao

Aerospace 2023, 10(9), 821; https://doi.org/10.3390/aerospace10090821 - 21 Sep 2023

Cited by 6 | Viewed by 2166

Abstract

Joints are widely used in large deployable structures but show semi-rigidity due to performance degradation and some nonlinear factors affecting the structure’s dynamic characteristics. This paper investigates the influence of semi-rigid joints on the characteristics of deployable structures in orbit. A virtual connection [...] Read more.

Joints are widely used in large deployable structures but show semi-rigidity due to performance degradation and some nonlinear factors affecting the structure’s dynamic characteristics. This paper investigates the influence of semi-rigid joints on the characteristics of deployable structures in orbit. A virtual connection element of three DOFs is proposed to model the semi-rigid joints. The governing equations of semi-rigid joints are established and integrated into the dynamic equation of the structures. A series of numerical experiments are carried out to validate the proposed model’s accuracy and efficiency, and the deployable truss structures’ static and dynamic responses are analyzed. The results show that semi-rigid joints exacerbate the effects of an in-orbit microvibration on the stability of deployable truss structures. Semi-rigid joints lower the dominant frequencies of structures, leading to a ‘closely-spaced-frequencies’ phenomenon and altering the dynamic responses significantly. The effects of semi-rigid joints on deployable truss structures are long-term and can be used to establish a relationship model between structural performance and service life. Nonlinear effects vary with the external load and depend on the structures’ instantaneous status. These results indicate that semi-rigid joints significantly influence the characteristics of deployable structures, which must be considered in the design and analysis of high-precision in-orbit deployable structures. Full article

(This article belongs to the Special Issue Design and Analysis of Advanced Composites and Structures in Aerospace)

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21 pages, 5338 KiB

Open AccessArticle

An Improved Multi-Objective Particle Swarm Optimization Method for Rotor Airfoil Design

by Yongchuan Wu, Gang Sun and Jun Tao

Aerospace 2023, 10(9), 820; https://doi.org/10.3390/aerospace10090820 - 20 Sep 2023

Cited by 3 | Viewed by 1395

Abstract

In this study, a multi-objective aerodynamic optimization is performed on the rotor airfoil via an improved MOPSO (multi-objective particle swarm optimization) method. A database of rotor airfoils containing both geometric and aerodynamic parameters is established, where the geometric parameters are obtained via the [...] Read more.

In this study, a multi-objective aerodynamic optimization is performed on the rotor airfoil via an improved MOPSO (multi-objective particle swarm optimization) method. A database of rotor airfoils containing both geometric and aerodynamic parameters is established, where the geometric parameters are obtained via the CST (class shape transformation) method and the aerodynamic parameters are obtained via CFD (computational fluid dynamics) simulations. On the basis of the database, a DBN (deep belief network) surrogate model is proposed and trained to accurately predict the aerodynamic parameters of the rotor airfoils. In order to improve the convergence rate and global searching ability of the standard MOPSO algorithm, an improved MOPSO framework is established. By embedding the DBN surrogate model into the improved MOPSO framework, multi-objective and multi-constraint aerodynamic optimization for the rotor airfoil is performed. Finally, the aerodynamic performance of the optimized rotor airfoil is validated through CFD simulations. The results indicate that the aerodynamic performance of the optimized rotor airfoil is improved dramatically compared with the baseline rotor airfoil. Full article

(This article belongs to the Special Issue E-VTOL Simulation and Autonomous System Development)

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16 pages, 4335 KiB

Open AccessArticle

Bibliometric Analysis of Engine Vibration Detection

by Mai Xin, Zhifeng Ye, Tong Zhang and Xiong Pan

Aerospace 2023, 10(9), 819; https://doi.org/10.3390/aerospace10090819 - 20 Sep 2023

Viewed by 1499

Abstract

After many years of development, the technology of analyzing the working condition of power units based on vibration signals has received relatively stable applications, but the accuracy and the degree of automation and intelligence for fault diagnosis are still inadequate due to the [...] Read more.

After many years of development, the technology of analyzing the working condition of power units based on vibration signals has received relatively stable applications, but the accuracy and the degree of automation and intelligence for fault diagnosis are still inadequate due to the limitations in the ongoing development of key technologies. With the development of big data and artificial intelligence technology, the involvement of new technologies will be an important boost to the development of this field. In this study, in order to support subsequent research, bibliometrics is used as a tool to sort the development of the technology in this field at the macro level. At the micro level, key publications in the literature are studied to better understand the development status at the technical level and prepare for the selection of entry points to facilitate in-depth innovation in the future. Full article

(This article belongs to the Topic Structural Health Monitoring and Non-Destructive Testing for Large-Scale Structures (2nd Edition))

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15 pages, 3392 KiB

Open AccessArticle

Using the Impulse Method to Determine High-Pressure Dynamic Burning Rate of Solid Propellants

by Jiahao Liu, Yinghong Wang, Xinyang Li and Junhao Cong

Aerospace 2023, 10(9), 818; https://doi.org/10.3390/aerospace10090818 - 18 Sep 2023

Cited by 2 | Viewed by 2252

Abstract

A new method for determining the burning rate of a solid propellant, called the Impulse Method, is proposed in this paper. It is based on the proportional relationship between the impulse generated and the mass of the burned propellant. The pressure–time and thrust–time [...] Read more.

A new method for determining the burning rate of a solid propellant, called the Impulse Method, is proposed in this paper. It is based on the proportional relationship between the impulse generated and the mass of the burned propellant. The pressure–time and thrust–time curves are obtained from a tubular propellant grain burning in the chamber, whose inner surface serves as the initial burning surface. Consequently, the mass of the propellant that was burned off at different pressures can be determined, and the burning rates at different pressures are derived according to the geometric parameters of the propellant grain. The Impulse Method was applied to test the burning rate of two types of propellants twice. The results show that the burning rates were consistent for the same propellant at corresponding pressures, demonstrating the feasibility and reliability of the Impulse Method. The burning rate of a GAP-based composite propellant at 20 MPa measured using the Standard Motor Method was 22.6 mm/s, and that measured using the Impulse Method was 22.2 mm/s and 22.7 mm/s, respectively. These findings indicate that the two methods have comparable accuracy. However, the Impulse Method has the advantage of obtaining the burning rate of the solid propellant at any pressure through a single test. In addition, the nozzle erosion only affected the pressure and not the burning rate. Finally, the rationality of the approach for determining the actual specific impulse was proven by comparing the results with those from another testing method. Full article

(This article belongs to the Special Issue Combustion Evaluation and Control of Solid Rocket Motors)

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24 pages, 25106 KiB

Open AccessArticle

Numerical Investigation of Stall Characteristics of Common Research Model Configuration Based on Zonal Detached Eddy Simulation Method

by Xin Zhang, Heng Zhang and Jie Li

Aerospace 2023, 10(9), 817; https://doi.org/10.3390/aerospace10090817 - 18 Sep 2023

Cited by 2 | Viewed by 1203

Abstract

A zonal detached eddy simulation (ZDES) method, based on the two-equation k-ω SST turbulence model, was employed to predict stall characteristics and capture small-scale vortex structures in the wake region of the main wing under the post-stall condition of the Common Research Model [...] Read more.

A zonal detached eddy simulation (ZDES) method, based on the two-equation k-ω SST turbulence model, was employed to predict stall characteristics and capture small-scale vortex structures in the wake region of the main wing under the post-stall condition of the Common Research Model (CRM) configuration. Additionally, the unsteady Reynolds-averaged Navier–Stokes (URANS) method was utilized for performance comparison in resolving small-scale vortices with ZDES. The results revealed a pronounced lateral flow on the wing, induced by the low-pressure region of the inner wing at post-stall angles of attack. Due to the downwash effect, the horizontal tail was influenced by the vortices in the wake region of the main wing, which the URANS method did not capture adequately. As the angle of attack increased, the separation area on the main wing expanded from the middle of the wing towards the inner wing. Consequently, the vortex structures in the wake region of the main wing became more intricate, and the primary peak of the lift coefficient spectrum shifted to the low-frequency region. Full article

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14 pages, 12396 KiB

Open AccessArticle

A Research on Rotor/Ship Wake Characteristics under Atmospheric Boundary Layer Conditions

by Guoqiang Li, Qing Wang, Qijun Zhao, Guoqing Zhao, Fei Feng and Linxin Wu

Aerospace 2023, 10(9), 816; https://doi.org/10.3390/aerospace10090816 - 18 Sep 2023

Viewed by 1201

Abstract

The environment for the shipboard landing and takeoff of helicopters is extremely complex and significantly affects their safe flight. To address the intricate characteristics of the flow field during these operations, a simulation method suitable for rotor/ship wake vortex interaction is developed. This [...] Read more.

The environment for the shipboard landing and takeoff of helicopters is extremely complex and significantly affects their safe flight. To address the intricate characteristics of the flow field during these operations, a simulation method suitable for rotor/ship wake vortex interaction is developed. This method couples the Delayed Detached Eddy Simulation (DDES) method and the momentum source method. The simulation of flow field characteristics of the SFS2 ship model under different conditions reveals that, in a rotor/ship coupling scenario, the inflow velocity in the wake zone of the flight deck is distributed in a “W” shape due to the influence of the rotor blade tip vortex. Under wind shear conditions, the rotor’s influence on the wake is reduced, resulting in smaller velocity fluctuations compared to uniform inflow conditions. Moreover, the detached eddy is suppressed to some extent. It can be concluded that shear flow mitigates the unsteady characteristics of the ship’s wake zone to some extent, which is beneficial to helicopter operations during takeoff and landing. Full article

(This article belongs to the Section Aeronautics)

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1 pages, 143 KiB

Open AccessArticle

RETRACTED: A 6U CubeSat Platform for Low Earth Remote Sensing: DEWASAT-2 Mission Concept and Analysis

by Ann Mary Eapen, Sidi Ahmed Bendoukha, Reem Al-Ali and Abdulrahman Sulaiman

Aerospace 2023, 10(9), 815; https://doi.org/10.3390/aerospace10090815 - 18 Sep 2023

Cited by 2 | Viewed by 2970 | Retraction

Abstract

Full article

17 pages, 24047 KiB

Open AccessArticle

Bridging the Gap between Simulation and Real Autonomous UAV Flights in Industrial Applications

by Rafael Perez-Segui, Pedro Arias-Perez, Javier Melero-Deza, Miguel Fernandez-Cortizas, David Perez-Saura and Pascual Campoy

Aerospace 2023, 10(9), 814; https://doi.org/10.3390/aerospace10090814 - 17 Sep 2023

Cited by 1 | Viewed by 1924

Abstract

The utilization of autonomous unmanned aerial vehicles (UAVs) has increased rapidly due to their ability to perform a variety of tasks, including industrial inspection. Conducting testing with actual flights within industrial facilities proves to be both expensive and hazardous, posing risks to the [...] Read more.

The utilization of autonomous unmanned aerial vehicles (UAVs) has increased rapidly due to their ability to perform a variety of tasks, including industrial inspection. Conducting testing with actual flights within industrial facilities proves to be both expensive and hazardous, posing risks to the system, the facilities, and their personnel. This paper presents an innovative and reliable methodology for developing such applications, ensuring safety and efficiency throughout the process. It involves a staged transition from simulation to reality, wherein various components are validated at each stage. This iterative approach facilitates error identification and resolution, enabling subsequent real flights to be conducted with enhanced safety after validating the remainder of the system. Furthermore, this article showcases two use cases: wind turbine inspection and photovoltaic plant inspection. By implementing the suggested methodology, these applications were successfully developed in an efficient and secure manner. Full article

(This article belongs to the Special Issue UAV Path Planning and Navigation)

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19 pages, 11883 KiB

Open AccessArticle

Electric Aerospace Actuator Manufactured by Laser Powder Bed Fusion

by Borja Lizarribar, Borja Prieto, Miren Aristizabal, Jose Manuel Martín, Miguel Martínez-Iturralde, Ekain San José, Ione Golvano and Sergio Montes

Aerospace 2023, 10(9), 813; https://doi.org/10.3390/aerospace10090813 - 17 Sep 2023

Cited by 1 | Viewed by 1834

Abstract

Recent advances in manufacturing methods have accelerated the exploration of new materials and advantageous shapes that could not be produced by traditional methods. In this context, additive manufacturing is gaining strength among manufacturing methods for its versatility and freedom in the geometries that [...] Read more.

Recent advances in manufacturing methods have accelerated the exploration of new materials and advantageous shapes that could not be produced by traditional methods. In this context, additive manufacturing is gaining strength among manufacturing methods for its versatility and freedom in the geometries that can be produced. Taking advantage of these possibilities, this research presents a case study involving an electric aerospace actuator manufactured using additive manufacturing. The main objectives of this research work are to assess the feasibility of additively manufacturing electric actuators and to evaluate potential gains in terms of weight, volume, power consumption and cost over conventional manufacturing technologies. To do so and in order to optimise the actuator design, a thorough material study is conducted in which three different magnetic materials are gas-atomised (silicon iron, permendur and supermalloy) and test samples of the most promising materials (silicon iron and permendur) are processed by laser powder bed fusion. The final actuator design is additively manufactured in permendur for the stator and rotor iron parts and in 316L stainless steel for the housing. The electric actuator prototype is tested, showing compliance with design requirements in terms of torque production, power consumption and heating. Finally, a design intended to be manufactured via traditional methods (i.e., punching and stacking for the stator laminations and machining for the housing) is presented and compared to the additively manufactured design. The comparison shows that additive manufacturing is a viable alternative to traditional manufacturing for the application presented, as it highly reduces the weight of the actuator and facilitates the assembly, while the cost difference between the two designs is minimal. Full article

(This article belongs to the Special Issue Metal Additive Manufacturing for Aerospace Applications)

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20 pages, 4913 KiB

Open AccessArticle

Investigation of Harmonic Response in Non-Premixed Swirling Combustion to Low-Frequency Acoustic Excitations

by Jinrong Bao, Chenzhen Ji, Deng Pan, Chao Zong, Ziyang Zhang and Tong Zhu

Aerospace 2023, 10(9), 812; https://doi.org/10.3390/aerospace10090812 - 15 Sep 2023

Cited by 1 | Viewed by 1347

Abstract

The propagation mechanism of flow disturbance under acoustic excitations plays a crucial role in thermoacoustic instability, especially when considering the effect of non-premixed combustion on heat release due to reactant mixing and diffusion. This relationship leads to a complex coupling between the spatial [...] Read more.

The propagation mechanism of flow disturbance under acoustic excitations plays a crucial role in thermoacoustic instability, especially when considering the effect of non-premixed combustion on heat release due to reactant mixing and diffusion. This relationship leads to a complex coupling between the spatial distribution of the equivalence ratio and the propagation mechanism of flow disturbance. In the present study, the response of a methane-air non-premixed swirling flame to low-frequency acoustic excitations was investigated experimentally. By applying Proper Orthogonal Decomposition (POD) analysis to CH* chemiluminescence images, the harmonic flame response was revealed. Large Eddy Simulation (LES) was utilized to analyze the correlation between the vortex motion within the shear layers and the harmonic response under non-reacting conditions at excitation frequencies of 20 Hz, 50 Hz, and 150 Hz. The results showed that the harmonic flame response was mainly due to the harmonic velocity pulsations within the shear layers. The acoustically induced vortices within the shear layer exhibited motion patterns susceptible to harmonic interference, with spatial distribution characteristics closely related to the oscillation modes of the non-premixed combustion. Full article

(This article belongs to the Special Issue Predicting the Onset and Control of Thermoacoustics)

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28 pages, 10170 KiB

Open AccessArticle

3D Soft-Landing Dynamic Theoretical Model of Legged Lander: Modeling and Analysis

by Zhiyi Wang, Chuanzhi Chen, Jinbao Chen and Guang Zheng

Aerospace 2023, 10(9), 811; https://doi.org/10.3390/aerospace10090811 - 15 Sep 2023

Cited by 2 | Viewed by 1656

Abstract

In this paper, a novel 3D (three-dimensional) soft-landing dynamic theoretical model of a legged lander is developed in detail as well as its numerical solution process. The six degrees of freedom motion (6-DOF) of the base model of the lander with mass center [...] Read more.

In this paper, a novel 3D (three-dimensional) soft-landing dynamic theoretical model of a legged lander is developed in detail as well as its numerical solution process. The six degrees of freedom motion (6-DOF) of the base model of the lander with mass center offset setting is considered in the model as well as the spatial motion (3-DOF) of each landing gear. The characteristics of the buffering force, the footpad–ground contact, and the inter-structure friction are also taken into account during the motion of each landing gear. The direct constraint violation correction is used to control the constraint stabilization of the nonlinear dynamic equation. Comparative studies between the results from the proposed model and the simulated model (built in MSC Adams) under four classical load cases show the validity of the model. Additionally, the influences of different types of contact force models, friction force models, and a friction correction model used in the soft-landing dynamic model are further investigated as a step toward understanding the soft-landing dynamic performance and the feasibility of the dynamic model method of a legged lander. The results indicate that a precise lateral force model of the footpad–ground contact is necessary to obtain the soft-landing performance of one lander during soft landing. Full article

(This article belongs to the Special Issue Advances in Entry, Descent, and Landing (EDL) for Planetary Exploration)

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24 pages, 9154 KiB

Open AccessArticle

Effect of Bending Deformation on the Lateral Force of Spinning Projectiles with Large Aspect Ratio

by Qi Liu, Juanmian Lei, Yong Yu and Jintao Yin

Aerospace 2023, 10(9), 810; https://doi.org/10.3390/aerospace10090810 - 15 Sep 2023

Cited by 1 | Viewed by 1087

Abstract

The bending deformation can affect the lateral force of spinning projectiles with large aspect ratios, thus interfering with their flight stability. Based on the established spin–deformation coupling motion model, the unsteady Reynolds averaged Navier–Stokes (URANS) equations are solved to simulate the flow over [...] Read more.

The bending deformation can affect the lateral force of spinning projectiles with large aspect ratios, thus interfering with their flight stability. Based on the established spin–deformation coupling motion model, the unsteady Reynolds averaged Navier–Stokes (URANS) equations are solved to simulate the flow over a large−aspect−ratio projectile undergoing spin and spin−deformation coupling motion by using the dual−time stepping method and dynamic mesh technique, obtaining the lateral force. Furtherly, the flow mechanism is analyzed for the changed lateral force induced by the bending deformation. The results indicate that the variation of transient lateral force for the head of a projectile is consistent with that of the deformation−induced additional sideslip angle; affected by the deformation−induced compression wave and expansion wave, the time−averaged lateral force for the middle of a projectile will be increased at small angles of attack, but changed little at large angles of attack; at small angles of attack, the change trend of transient lateral force for the tail of a projectile is similar to that of additional angle of attack caused by the deformation; at large angles of attack, the characteristic of phase lag is presented between the transient lateral force for the tail of a projectile and the additional sideslip angle. Full article

(This article belongs to the Special Issue Fluid Flow Mechanics (3rd Edition))

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22 pages, 9509 KiB

Open AccessArticle

On the Aeroelasticity of a Cantilever Wing Equipped with the Spanwise Morphing Trailing Edge Concept

by Jafar S. Pilakkadan, Rafic M. Ajaj, Zawar Haider and Mohammadreza Amoozgar

Aerospace 2023, 10(9), 809; https://doi.org/10.3390/aerospace10090809 - 15 Sep 2023

Cited by 1 | Viewed by 1635

Abstract

This paper studies the aeroelastic behavior of a rectangular, cantilever wing equipped with the spanwise morphing trailing edge (SMTE) concept. The SMTE consists of multiple trailing edge flaps that allow controlling the spanwise camber distribution of a wing. The flaps are attached at [...] Read more.

This paper studies the aeroelastic behavior of a rectangular, cantilever wing equipped with the spanwise morphing trailing edge (SMTE) concept. The SMTE consists of multiple trailing edge flaps that allow controlling the spanwise camber distribution of a wing. The flaps are attached at the wing’s trailing edge using torsional springs. The Rayleigh–Ritz method is used to develop the equations of motion of the wing-flap system. The use of shape functions allows for representing the wing as an equivalent 2D airfoil with generalized coordinates that are defined at the wingtip. Strip theory, based on Theodorsen’s unsteady aerodynamic model, is used to compute the aerodynamic loads acting on the wing. A representative Padé approximation for Theodorsen’s function is utilized to model the aerodynamic behaviors in a state-space form allowing time-domain simulation and analysis. The model is validated using a rectangular cantilever wing and the data are available in the literature. A comprehensive parametric comparison study is conducted to assess the impact of flap stiffness on the aeroelastic boundary. In addition, the potential of the SMTE to provide load alleviation and flutter suppression is assessed for a wide range of flight conditions, using a discrete (1-cosine) gust. Finally, the implementation and validation of a controller for a wing with SMTE for gust load alleviation are studied and controller parameters are tuned for a specific gust model. Full article

(This article belongs to the Special Issue Applied Aeroelasticity and Fluid-Structure Interaction)

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14 pages, 4686 KiB

Open AccessArticle

A Turbulent Inflow Generation Method for the LES of High Re Flow by Scaling Low Re Flow Data

by Lei Luo and Honghu Ji

Aerospace 2023, 10(9), 808; https://doi.org/10.3390/aerospace10090808 - 15 Sep 2023

Cited by 1 | Viewed by 1056

Abstract

The rescaling–recycling method (RRM) is usually used to generate turbulent inflow for the LES of compressible wall-bounded flows, which can lead to relatively high computational cost for high Re flows since the mesh resolution increases exponentially with Re number. A turbulent inflow generation [...] Read more.

The rescaling–recycling method (RRM) is usually used to generate turbulent inflow for the LES of compressible wall-bounded flows, which can lead to relatively high computational cost for high Re flows since the mesh resolution increases exponentially with Re number. A turbulent inflow generation method based on the scaling of low Re flow, referred as TIG-LowRe, is proposed, aiming at reducing the computational cost when applying the RRM. To validate the proposed method, the TIG-LowRe method was applied to generate turbulent inflow for the LES of a non-isothermal round jet flow at Re = 86,000. Two cases were carried out with the inflow generated based on two round pipe flows at Re = 10,000 and 24,000. The results show that the mean and fluctuating temperatures of the two cases agree well with the experimental data. In the case of low Re flow at Re = 10,000, the jet flow decays too fast along the axial direction, the mean and fluctuating axial velocities are over-predicted and the radial fluctuating velocity is under-predicted. By increasing the Re of the low Re flow to 24,000, the decay rate of the jet flow decreases and the accuracies of the mean and fluctuating axial velocities are obviously improved, while the radial fluctuating velocity shifts further away from the experimental data. The main reason for the difference between the two cases is that more fine turbulent structure of the inflow in case-Re10000 is lost than in case-Re24000 during the turbulence generation process. Full article

(This article belongs to the Section Aeronautics)

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27 pages, 4254 KiB

Open AccessArticle

A Study on the Derivation of Atmospheric Water Vapor Based on Dual Frequency Radio Signals and Intersatellite Communication Networks

by Ramson Munyaradzi Nyamukondiwa, Necmi Cihan Orger, Daisuke Nakayama and Mengu Cho

Aerospace 2023, 10(9), 807; https://doi.org/10.3390/aerospace10090807 - 15 Sep 2023

Cited by 2 | Viewed by 1544

Abstract

The atmospheric total water vapor content (TWVC) affects climate change, weather patterns, and radio signal propagation. Recent techniques such as global navigation satellite systems (GNSS) are used to measure TWVC but with either compromised accuracy, temporal resolution, or spatial coverage. This [...] Read more.

The atmospheric total water vapor content (TWVC) affects climate change, weather patterns, and radio signal propagation. Recent techniques such as global navigation satellite systems (GNSS) are used to measure TWVC but with either compromised accuracy, temporal resolution, or spatial coverage. This study demonstrates the feasibility of predicting, mapping, and measuring TWVC using spread spectrum (SS) radio signals and software-defined radio (SDR) technology on low Earth-orbiting (LEO) satellites. An intersatellite link (ISL) communication network from a constellation of small satellites is proposed to achieve three-dimensional (3D) mapping of TWVC. However, the calculation of TWVC from satellites in LEO contains contribution from the ionospheric total electron content (TEC). The TWVC and TEC contribution are determined based on the signal propagation time delay and the satellites’ positions in orbit. Since TEC is frequency dependent unlike TWVC, frequency reconfiguration algorithms have been implemented to distinguish TWVC. The novel aspects of this research are the implementation of time stamps to deduce time delay, the unique derivation of TWVC from a constellation setup, the use of algorithms to remotely tune frequencies in real time, and ISL demonstration using SDRs. This mission could contribute to atmospheric science, and the measurements could be incorporated into the global atmospheric databases for climate and weather prediction models. Full article

(This article belongs to the Special Issue Small Satellite Missions)

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28 pages, 7796 KiB

Open AccessArticle

Parameter Identification of Pilot Model and Stability Analysis of Human-in-Loop Image Seeker

by Yi Zhang, Tao Li, Yanning Li and Gen Wang

Aerospace 2023, 10(9), 806; https://doi.org/10.3390/aerospace10090806 - 15 Sep 2023

Cited by 1 | Viewed by 1266

Abstract

In the human-in-loop (HIL) guidance mode, a pilot quickly identifies and flexibly locks on to a target through a real-time image signal transmitted by the aircraft. Then, the line-of-sight (LOS) angle error in the viewing field is tracked and compensated for in order [...] Read more.

In the human-in-loop (HIL) guidance mode, a pilot quickly identifies and flexibly locks on to a target through a real-time image signal transmitted by the aircraft. Then, the line-of-sight (LOS) angle error in the viewing field is tracked and compensated for in order to improve the guidance and control performance of the image-guided aircraft. Based on the physical structure and device parameters of the image seeker, an appropriate correction network is designed to improve the performance of the seeker stability loop. Aiming at a precise-extended crossover (PEC) pilot model, the structure of the dynamic model is optimized, and the maximum likelihood estimation (MLE) method of the output error structure is used to identify the dynamic parameters. This makes up for the deficiency of the existing modeling. In order to solve the nonlinear optimization problems encountered in the identification process, a hybrid strategy of a genetic algorithm (GA) and Gauss–Newton optimization algorithm is used to improve the probability of finding the global optimal solution. The simplex method is also used to improve the robustness of the algorithm. In addition, a hardware-in-the-loop simulation is designed and multi-round HIL experiment flow is performed. Moreover, based on the adaptability of the pilot to different image signal delays, the effects of different image signal delays on the stability and disturbance rejection rate (DRR) of the seeker control system are studied. The results demonstrate that the hybrid gradient optimization algorithm (HGOA) can find the global optimal value, and the identification model can accurately reflect the dynamic characteristics of the pilot. In the HIL guidance mode, the tracking compensation behavior of the pilot can reduce the influence of image signal delay on the disturbance of the aircraft body isolated by the seeker. The optimized PEC model and the identified dynamic parameters improve the efficiency of pilot training and screening. Full article

(This article belongs to the Section Aeronautics)

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15 pages, 7945 KiB

Open AccessArticle

The Development and Application of Two-Color Pressure-Sensitive Paint in Jet Impingement Experiments

by Wei-Chieh Chen, Chih-Yung Huang, Kui-Thong Tan and Hirotaka Sakaue

Aerospace 2023, 10(9), 805; https://doi.org/10.3390/aerospace10090805 - 15 Sep 2023

Cited by 1 | Viewed by 1191

Abstract

This study aimed to develop a two-color pressure-sensitive paint (PSP) that has both high pressure sensitivity and high temperature sensitivity. Different nitrobenzoxadiazole (NBD) derivatives were used as the temperature probe. Among them, NBD-ZY37 demonstrated favorable stability against photodegradation, and its temperature sensitivity in [...] Read more.

This study aimed to develop a two-color pressure-sensitive paint (PSP) that has both high pressure sensitivity and high temperature sensitivity. Different nitrobenzoxadiazole (NBD) derivatives were used as the temperature probe. Among them, NBD-ZY37 demonstrated favorable stability against photodegradation, and its temperature sensitivity in an RTV118-based two-color PSP was −1.4%/°C. Moreover, temperature sensitivity was independent of pressure in the tested temperature range. PtTFPP was used, and its pressure sensitivity was measured to be 0.5% per kPa. The two-color PSP paint underwent further examination in jet impingement experiments. The experimental results indicated that the pressure fluctuation introduced by the shock waves occurred earlier at higher impingement angles. Specifically, when the pressure ratio was 2.38, increasing the impinging angle from 15° to 30° caused the location of the pressure wave to move from s/D at 0.8 to the exit of the nozzle. Simultaneously, the shape of the maximum pressure zone changed from a fan shape to a round shape. Additionally, the jet region expanded when the pressure ratio was increased. Full article

(This article belongs to the Section Aeronautics)

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27 pages, 5793 KiB

Open AccessArticle

Task Offloading with Data-Dependent Constraints in Satellite Edge Computing Networks: A Multi-Objective Approach

by Ruipeng Zhang, Yanxiang Feng, Yikang Yang and Xiaoling Li

Aerospace 2023, 10(9), 804; https://doi.org/10.3390/aerospace10090804 - 14 Sep 2023

Cited by 1 | Viewed by 1730

Abstract

By enabling a satellite network with edge computing capabilities, satellite edge computing(SEC) provides users with a full range of computing service. In this paper, we construct a multi-objective optimization model for task offloading with data-dependent constraints in an SEC network and aim to [...] Read more.

By enabling a satellite network with edge computing capabilities, satellite edge computing(SEC) provides users with a full range of computing service. In this paper, we construct a multi-objective optimization model for task offloading with data-dependent constraints in an SEC network and aim to achieve optimal tradeoffs among energy consumption, cost, and makespan. However, dependency constraints between tasks may lead to unexpected computational delays and even task failures in an SEC network. To solve this, we proposed a Petri-net-based constraint amending method with polynomial complexity and generated offloading results satisfying our constraints. For the multiple optimization objectives, a strengthened dominance relation sort was established to balance the convergence and diversity of nondominated solutions. Based on these, we designed a multi-objective wolf pack search (MOWPS) algorithm. A series of adaptive mechanisms was employed for avoiding additional computational overhead, and a Lamarckian-learning-based multi-neighborhood search prevents MOWPS from becoming trapped in the local optimum. Extensive computational experiments demonstrate the outperformance of MOWPS for solving task offloading with data-dependent constraints in an SEC network. Full article

(This article belongs to the Special Issue Space-Air-Ground-Integrated Communications in the New Era: Applications, Challenges, and Countermeasures)

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17 pages, 1352 KiB

Open AccessArticle

Preliminary Analysis of the Performance of an Electric Supersonic Propeller

by Jens Kunze and Allan Paull

Aerospace 2023, 10(9), 803; https://doi.org/10.3390/aerospace10090803 - 14 Sep 2023

Cited by 1 | Viewed by 1471

Abstract

A preliminary aerodynamic and thermodynamic analysis of a supersonic propeller driven by an electric motor is performed. The analysis is aimed at determining whether such a system is feasible and further and more detailed investigation is warranted. Recent progress in electric energy storage [...] Read more.

A preliminary aerodynamic and thermodynamic analysis of a supersonic propeller driven by an electric motor is performed. The analysis is aimed at determining whether such a system is feasible and further and more detailed investigation is warranted. Recent progress in electric energy storage and motors, as well as high temperature and lightweight materials, has opened up the design space for a large number of applications. Electrically powered flight and propellers are among these applications. This study shows that very good aerodynamic and propulsive efficiencies can be achieved with this combination. In this paper, the design space of supersonic propeller blades is explored and the effect of a number of design parameters on the blade efficiency is shown. Further analysis is performed to demonstrate that reasonable efficiency can be achieved at flight Mach numbers from two to six between 15 and 35 km altitude. Finally, a mission-based propeller design study is performed to demonstrate practical system performance and show trade-offs between different parameters. Full article

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24 pages, 43640 KiB

Open AccessArticle

Neck Structure Optimal Design of the Turbine Wheel for Containment Design of the Air Turbine Starter

by Liqiang Chen, Haijun Xuan, Wenbin Jia, Jianxin Liu, Zehui Fang and Yao Zheng

Aerospace 2023, 10(9), 802; https://doi.org/10.3390/aerospace10090802 - 14 Sep 2023

Cited by 3 | Viewed by 1535

Abstract

The airworthiness standards of the transport category airplanes stipulate that the high energy rotor equipment must be of the sufficient containment capacity. It is of great importance to study the containment and weight reduction for the air turbine starter. In this paper, based [...] Read more.

The airworthiness standards of the transport category airplanes stipulate that the high energy rotor equipment must be of the sufficient containment capacity. It is of great importance to study the containment and weight reduction for the air turbine starter. In this paper, based on an OSF design, Kriging response surface model and MOGA algorithm, a neck structure optimal design method was proposed for the air turbine wheel. Using the optimal design method, the optimal structural parameters were suggested as the design parameters, and verified by the over-speed burst test. The maximum errors of the burst speeds between the experimental and design values are less than 2%, and the neck structure turbine wheel breaks in the neck as expected, validating the accuracy of the optimal design method. Then, the effects of turbine wheel burst modes on the containment were investigated quantitatively, and verified by the containment tests. Based on the experimental and simulation results, the containment design method was proposed for the neck structure turbine wheel. The results show that compared with the trisection wheel burst, the rim burst dramatically decrease the mass and initial kinetic energy of burst released fragments by 63.3% and 24.8%, thereby greatly reducing the thickness and the mass of the containment ring by 29.5% and 29.1%. Full article

(This article belongs to the Section Aeronautics)

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13 pages, 1059 KiB

Open AccessArticle

Aeroelasticity Model for Highly Flexible Aircraft Based on the Vortex Lattice Method

by Mindaugas Dagilis and Sigitas Kilikevičius

Aerospace 2023, 10(9), 801; https://doi.org/10.3390/aerospace10090801 - 14 Sep 2023

Viewed by 1526

Abstract

With the increasing use of composite materials in aviation, structural aircraft design often becomes limited by stiffness, rather than strength. As a consequence, aeroelastic analysis becomes more important to optimize both aircraft structures and control algorithms. A low computational cost aeroelasticity model based [...] Read more.

With the increasing use of composite materials in aviation, structural aircraft design often becomes limited by stiffness, rather than strength. As a consequence, aeroelastic analysis becomes more important to optimize both aircraft structures and control algorithms. A low computational cost aeroelasticity model based on VLM and rigid-body dynamics is proposed in this work. UAV flight testing is performed to evaluate the accuracy of the proposed model. Two flight sections are chosen to be modeled based on recorded aerodynamic surface control data. The calculated accelerations are compared with recorded flight data. It is found that the proposed model adequately captures the general flight profile, with acceleration peak errors between −6.2% and +8.4%. The average relative error during the entire flight section is 39% to 44%, mainly caused by rebounds during the beginning and end of pull-up maneuvers. The model could provide useful results for the initial phases of aircraft control law design when comparing different control algorithms. Full article

(This article belongs to the Special Issue Multiscale Modelling in Aerospace Engineering)

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12 pages, 12583 KiB

Open AccessArticle

Combustion Characteristics of HTPB-Based Hybrid Rocket Fuels: Using Nickel Oxide as the Polymer Matrix Pyrolysis Catalyst

by Hongsheng Yu, Xiaodong Yu, Hongwei Gao, Luigi T. DeLuca, Wei Zhang and Ruiqi Shen

Aerospace 2023, 10(9), 800; https://doi.org/10.3390/aerospace10090800 - 13 Sep 2023

Cited by 1 | Viewed by 1863

Abstract

The slow regression rate induced by the high pyrolysis difficulty has limited the application and development of hydroxyl-terminated polybutadiene (HTPB)-based fuels in hybrid rocket propulsion. Nickel oxide (NiO) shows the possibility of increasing the regression rate of HTPB-based fuels by catalyzing the pyrolysis [...] Read more.

The slow regression rate induced by the high pyrolysis difficulty has limited the application and development of hydroxyl-terminated polybutadiene (HTPB)-based fuels in hybrid rocket propulsion. Nickel oxide (NiO) shows the possibility of increasing the regression rate of HTPB-based fuels by catalyzing the pyrolysis process of the polymer matrix in our previous investigation; hence, this paper studies the NiO particles in the thermal decomposition and combustion of HTPB fuel grains. The DSC/TG test shows that NiO can intensely decrease the thermal stability of HTPB, and the catalytic effect of NiO is mainly reflected in the final decomposition stages of polybutadiene components. 5 wt% NiO enhances the regression rate by 19.4% and 13.7% under an oxygen mass flux of 50 kg/m²s and 150 kg/m²s, respectively. Further investigation shows that NiO particles will also cause the reduction of combustion heat and the agglomeration at the regressing surface while catalyzing the pyrolysis process, improving the thermal conductivity, and promoting the radiative heat transfer of the HTPB-based fuels; thus, more NiO additive (5 wt% < [NiO] ≤ 10 wt%) does not lead to a faster regression rate in HTPB-based fuels. This study demonstrates the catalytic effect of NiO on the polymer matrix for HTPB-based fuels, showing the attractive application prospects of this additive in HTPB-containing fuel grains. Full article

(This article belongs to the Special Issue Hybrid Rocket Engines)

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19 pages, 4013 KiB

Open AccessArticle

Suggestions for Criteria to Evaluate Lateral-Directional Nonlinear Pilot-Induced Oscillations Due to Fly-by-Wire Civil Aircraft Landing Configuration Switch

by Lixin Wang, Chang Lu, Tao Jin, Hailiang Liu and Ting Yue

Aerospace 2023, 10(9), 799; https://doi.org/10.3390/aerospace10090799 - 13 Sep 2023

Viewed by 1158

Abstract

Using a nonlinear pilot-induced oscillation prediction method based on digital virtual flight simulation calculations, digital experiments on predicting lateral-directional nonlinear pilot-induced oscillations due to landing configuration switching of fly-by-wire civil aircraft with different closed-loop dynamic characteristics are carried out. It is proposed that [...] Read more.

Using a nonlinear pilot-induced oscillation prediction method based on digital virtual flight simulation calculations, digital experiments on predicting lateral-directional nonlinear pilot-induced oscillations due to landing configuration switching of fly-by-wire civil aircraft with different closed-loop dynamic characteristics are carried out. It is proposed that the lateral-directional pilot-induced oscillations due to the landing configuration switch can be evaluated using the changes in dynamic characteristic parameters before and after the configuration switch. The quantitative boundaries of the dynamic characteristic parameters of an example aircraft are determined, and a criterion suggestion is formed to predict the lateral-directional nonlinear pilot-induced oscillations due to landing configuration switching. This study provides a reference for the optimal design of the lateral-directional flight control law of fly-by-wire aircraft during the approach stage and provides suggestions for the formulation of evaluation criteria for other nonlinear pilot-induced oscillation phenomena. Full article

(This article belongs to the Section Aeronautics)

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24 pages, 9454 KiB

Open AccessArticle

Response of the Shock Wave/Boundary Layer Interaction to Disturbances Induced by the Plasma Discharge

by Oleg Vishnyakov, Pavel Polivanov and Andrey Sidorenko

Aerospace 2023, 10(9), 798; https://doi.org/10.3390/aerospace10090798 - 13 Sep 2023

Cited by 1 | Viewed by 1679

Abstract

The paper focuses on the investigation of unsteady effects in shock wave/boundary layer interaction. The study was carried out using a flat plate model subjected to a free stream Mach number of 1.43 and a unit Reynolds number (Re₁) of 11.5 [...] Read more.

The paper focuses on the investigation of unsteady effects in shock wave/boundary layer interaction. The study was carried out using a flat plate model subjected to a free stream Mach number of 1.43 and a unit Reynolds number (Re₁) of 11.5 × 10⁶ 1/m. To generate two-dimensional disturbances in the laminar boundary layer upstream of the separation region, a dielectric barrier discharge was employed. The disturbances were generated within the frequency range of 500 to 1700 Hz. The Strouhal numbers based on the length of the separation bubble ranged from 0.04 to 0.13. The measurements were carried out using a hot-wire anemometer. Analysis of the data shows that disturbances in this frequency range mostly decay. The maximum amplitudes of perturbations were observed at frequencies of 1250 Hz and 1700 Hz. Full article

(This article belongs to the Special Issue Plasma Actuator)

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21 pages, 1862 KiB

Open AccessArticle

Adjoint and Direct Characteristic Equations for Two-Dimensional Compressible Euler Flows

by Kevin Ancourt, Jacques Peter and Olivier Atinault

Aerospace 2023, 10(9), 797; https://doi.org/10.3390/aerospace10090797 - 12 Sep 2023

Cited by 1 | Viewed by 1316

Abstract

The method of characteristics is a classical method for gaining understanding in the solution of a partial differential equation. It has recently been applied to the adjoint equations of the 2D steady-state Euler equations and the first goal of this paper is to [...] Read more.

The method of characteristics is a classical method for gaining understanding in the solution of a partial differential equation. It has recently been applied to the adjoint equations of the 2D steady-state Euler equations and the first goal of this paper is to present a linear algebra analysis that greatly simplifies the discussion of the number of independent characteristic equations satisfied along a family of characteristic curves. This method may be applied for both the direct and the adjoint problem. Our second goal is to directly derive in conservative variables the characteristic equations of 2D compressible inviscid flows. Finally, the theoretical results are assessed for a nozzle flow with a classical scheme and its dual consistent discrete adjoint. Full article

(This article belongs to the Special Issue Adjoint Method for Aerodynamic Design and Other Applications in CFD)

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22 pages, 14952 KiB

Open AccessArticle

A New Flow Control and Efficiency Enhancement Method for Horizontal Axis Wind Turbines Based on Segmented Prepositive Elliptical Wings

by Xuan Bai, Hao Zhan and Baigang Mi

Aerospace 2023, 10(9), 796; https://doi.org/10.3390/aerospace10090796 - 12 Sep 2023

Cited by 1 | Viewed by 1377

Abstract

Flow separation occurs when wind turbines operate under large inflow conditions, which seriously affects the utilization of wind energy and reduces the output power of the blade. Therefore, a composite flow control configuration for horizontal axis wind turbines, founded on segmented prepositive elliptical [...] Read more.

Flow separation occurs when wind turbines operate under large inflow conditions, which seriously affects the utilization of wind energy and reduces the output power of the blade. Therefore, a composite flow control configuration for horizontal axis wind turbines, founded on segmented prepositive elliptical wings, is proposed for efficiency enhancement. Taking a typical NREL Phase VI wind turbine as the prototype, its separation effect is evaluated by the CFD method. Then, starting from the improvement of the two-dimensional airfoil flow, the prepositive elliptic wing is designed according to the airfoil flow, and the optimal two-dimensional flow control configuration of the blade airfoil is obtained by simulation analysis. Finally, the two-dimensional configuration is extended to three-dimensional, and the aerodynamic characteristics of the blade before and after flow control are simulated and compared. The results show that, at wind speeds of 10~20 m/s, flow separation on the blade is effectively inhibited; meanwhile, the pressure difference between the pressure surface and the suction surface increases. These characteristics greatly improve the performance of wind turbine and increase its torque by more than 30%. Moreover, when the flow control effect cannot be reached, the blade torque is only reduced by approximately 2%. Full article

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Aerospace, Volume 10, Issue 9 (September 2023) – 90 articles

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