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Associate Professor Ir. Ts. Dr Parvathy Rajendran has been an academic in the School of Aerospace Engineering at Universiti Sains Malaysia since 2013. She completed her PhD in Aerospace Engineering from Cranfield University, the United Kingdom, in October 2012. Her research includes UAV design, development and flight testing, and UAV's systems development and testing. Rajendran has produced many high-impact publications and served as an editor-in-chief, guest editor, international advisor, and reviewer. She has been the chairman and member of the technical conference committee of various international conferences. She has also maintained various grants worth more than RM 1.7 million.
Despite years of work, a robust, widely applicable generic “symmetry detector” that can paral-lel other kinds of computer vision/image processing tools for the more basic structural charac-teristics, such as a “edge” or “corner” detector, remains a computational challenge. A new symmetry feature detector with a descriptor is proposed in this paper, namely the Simple Robust Features (SRF) algorithm. A performance comparison is made among SRF with SRF, Speeded-up Robust Features (SURF) with SURF, Maximally Stable Extremal Regions (MSER) with SURF, Harris with Fast Retina Keypoint (FREAK), Minimum Eigenvalue with FREAK, Features from Accelerated Segment Test (FAST) with FREAK, and Binary Robust Invariant Scalable Keypoints (BRISK) with FREAK. A visual tracking dataset is used in this performance evaluation in terms of accuracy and computational cost. The results have shown that combining the SRF detector with the SRF descriptor is preferable, as it has on average the highest accuracy. Additionally, the computational cost of SRF with SRF is much lower than the others.
Kai Kok; Parvathy Rajendran. A Descriptor-Based Advanced Feature Detector for Improved Visual Tracking. Symmetry 2021, 13, 1337 .
AMA StyleKai Kok, Parvathy Rajendran. A Descriptor-Based Advanced Feature Detector for Improved Visual Tracking. Symmetry. 2021; 13 (8):1337.
Chicago/Turabian StyleKai Kok; Parvathy Rajendran. 2021. "A Descriptor-Based Advanced Feature Detector for Improved Visual Tracking." Symmetry 13, no. 8: 1337.
Traditional Multi-Criteria Decision Making (MCDM) methods have now become outdated; therefore, most researchers are focusing on more robust hybrid MCDM models that combine two or more MCDM techniques to address decision-making problems. The authors attempted to create two novel hybrid MCDM systems in this paper by integrating Additive Ratio ASsessment (ARAS) with Technique for Order of Preference by Similarity to Ideal Solution (TOPSIS) and Complex PRoportional ASsessment (COPRAS). To demonstrate the ability and effectiveness of these two hybrid models i.e., TOPSIS-ARAS and COPRAS-ARAS were applied to solve a real-time robot selection problem with 12 alternative robots and five selection criteria, while evaluating the parametric importance using the CRiteria Importance Through Inter criteria Correlation (CRITIC) objective weighting estimation tool. The rankings of the robot alternatives gained from these two hybrid models were also compared to the obtained results from eight other solo MCDM tools. Although the rankings by the applied methods slightly differ from each other, the final outcomes from all of the adopted techniques are consistent enough to suggest that robot 12 is the best choice followed by robot 11, and robot 4 is the worst one among these 12 alternatives. Spearman Correlation Coefficient (SCC) also reveals that the proposed rankings derived from various methods have a strong ranking relationship with one another. Finally, sensitivity analysis was performed to investigate the effects of weight variation and to validate the robustness of the implemented MCDM approaches.
Shankha Goswami; Dhiren Behera; Asif Afzal; Abdul Razak Kaladgi; Sher Khan; Parvathy Rajendran; Ram Subbiah; Mohammad Asif. Analysis of a Robot Selection Problem Using Two Newly Developed Hybrid MCDM Models of TOPSIS-ARAS and COPRAS-ARAS. Symmetry 2021, 13, 1331 .
AMA StyleShankha Goswami, Dhiren Behera, Asif Afzal, Abdul Razak Kaladgi, Sher Khan, Parvathy Rajendran, Ram Subbiah, Mohammad Asif. Analysis of a Robot Selection Problem Using Two Newly Developed Hybrid MCDM Models of TOPSIS-ARAS and COPRAS-ARAS. Symmetry. 2021; 13 (8):1331.
Chicago/Turabian StyleShankha Goswami; Dhiren Behera; Asif Afzal; Abdul Razak Kaladgi; Sher Khan; Parvathy Rajendran; Ram Subbiah; Mohammad Asif. 2021. "Analysis of a Robot Selection Problem Using Two Newly Developed Hybrid MCDM Models of TOPSIS-ARAS and COPRAS-ARAS." Symmetry 13, no. 8: 1331.
Steam generation and utilization are needed in many industries and home appliances with, specific requirements. Though there are numerous categories of boilers available for steam generation, this analysis concentrated on the water tube boiler since it produces more steam and offers better safety measures. Taguchi techniques are considered in this entire research work completed through design of experiments (DOE). Orthogonal array L16 is selected to examine the steam generation with four process parameters and four levels. Selected process parameters are namely temperature of feed water (°C), the pressure of feed water (bar), cold water supply (liters), and boiler drum pressure (bar). The response of this study is the as steam generation to since increasing the steam is a target of this investigation. The experimental value of the steam generation is compared with the desired range; most of the response values are within the predicted value. Further, the superheated steam temperature and pressure analysis were also carried out. The maximum steam generation is achieved as 84.31 L; registered in the 15th run of the experiment.
T. Sathish; V. Mohanavel; Asif Afzal; M. Arunkumar; M. Ravichandran; Sher Afghan Khan; Parvathy Rajendran; Mohammad Asif. Advancement of steam generation process in water tube boiler using Taguchi design of experiments. Case Studies in Thermal Engineering 2021, 27, 101247 .
AMA StyleT. Sathish, V. Mohanavel, Asif Afzal, M. Arunkumar, M. Ravichandran, Sher Afghan Khan, Parvathy Rajendran, Mohammad Asif. Advancement of steam generation process in water tube boiler using Taguchi design of experiments. Case Studies in Thermal Engineering. 2021; 27 ():101247.
Chicago/Turabian StyleT. Sathish; V. Mohanavel; Asif Afzal; M. Arunkumar; M. Ravichandran; Sher Afghan Khan; Parvathy Rajendran; Mohammad Asif. 2021. "Advancement of steam generation process in water tube boiler using Taguchi design of experiments." Case Studies in Thermal Engineering 27, no. : 101247.
A numerical simulation of a patient’s nasal airflow was developed via computational fluid dynamics. Accordingly, computerized tomography scans of a patient with septal deviation and allergic rhinitis were obtained. The three-dimensional (3D) nasal model was designed using InVesalius 3.0, which was then imported to (computer aided 3D interactive application) CATIA V5 for modification, and finally to analysis system (ANSYS) flow oriented logistics upgrade for enterprise networks (FLUENT) to obtain the numerical solution. The velocity contours of the cross-sectional area were analyzed on four main surfaces: the vestibule, nasal valve, middle turbinate, and nasopharynx. The pressure and velocity characteristics were assessed at both laminar and turbulent mass flow rates for both the standardized and the patient’s model nasal cavity. The developed model of the patient is approximately half the size of the standardized model; hence, its velocity was approximately two times more than that of the standardized model.
Zi Fen Lim; Parvathy Rajendran; Muhamad Yusri Musa; Chih Fang Lee. Nasal airflow of patient with septal deviation and allergy rhinitis. Visual Computing for Industry, Biomedicine, and Art 2021, 4, 1 -11.
AMA StyleZi Fen Lim, Parvathy Rajendran, Muhamad Yusri Musa, Chih Fang Lee. Nasal airflow of patient with septal deviation and allergy rhinitis. Visual Computing for Industry, Biomedicine, and Art. 2021; 4 (1):1-11.
Chicago/Turabian StyleZi Fen Lim; Parvathy Rajendran; Muhamad Yusri Musa; Chih Fang Lee. 2021. "Nasal airflow of patient with septal deviation and allergy rhinitis." Visual Computing for Industry, Biomedicine, and Art 4, no. 1: 1-11.
This paper presents an optimization algorithm named Random Explosion Algorithm (REA). The fundamental idea of this algorithm is based on a simple concept of the explosion of an object. This object is commonly known as a particle: when exploded, it will randomly disperse fragments around the particle within the explosion radius. The fragment that will be considered as a search agent will fill the local space and search that particular region for the best fitness solution. The proposed algorithm was tested on 23 benchmark test functions, and the results are validated by a comparative study with eight well-known algorithms, which are Particle Swarm Optimization (PSO), Artificial Bee Colony (ABC), Genetic Algorithm (GA), Differential Evolution (DE), Multi-Verse Optimizer (MVO), Moth Flame Optimizer (MFO), Firefly Algorithm (FA), and Sooty Tern Optimization Algorithm (STOA). After that, the algorithm was implemented and analyzed for a quadrotor control application. Similarly, a comparative study with the other algorithms stated was done. The findings reveal that the REA can yield very competitive results. It also shows that the convergence analysis has proved that the REA can converge more quickly toward the global optimum than the other metaheuristic algorithms. For the control application result, the REA controller can better track the desired reference input with shorter rise time and settling time, lower percentage overshoot, and minimal steady-state error and root mean square error (RMSE).
Mohamad Shauqee; Parvathy Rajendran; Nurulasikin Suhadis. An Explosion Based Algorithm to Solve the Optimization Problem in Quadcopter Control. Aerospace 2021, 8, 125 .
AMA StyleMohamad Shauqee, Parvathy Rajendran, Nurulasikin Suhadis. An Explosion Based Algorithm to Solve the Optimization Problem in Quadcopter Control. Aerospace. 2021; 8 (5):125.
Chicago/Turabian StyleMohamad Shauqee; Parvathy Rajendran; Nurulasikin Suhadis. 2021. "An Explosion Based Algorithm to Solve the Optimization Problem in Quadcopter Control." Aerospace 8, no. 5: 125.
The usage of slots has gained renewed interest in aerospace, particularly on propeller design. Most of the works have focused on improving the aerodynamic performance and efficiency. Modern research on propeller design aims to design propellers with high thrust performance under low torque conditions without any weight penalty. Although research on slotted design has been done before, none has been done to understand its impact on different airfoils on the propeller blade. Thus, this study aims to provide extensive research on slotted propeller design with various airfoil of different properties such as high Reynolds number, low Reynolds number, symmetrical, asymmetrical high lift, and low drag. This work has been investigated using computational fluid dynamics method to predict propeller performance for a small-scale propeller. The slotted blade designs' performance is presented in terms of thrust coefficient, power coefficient, efficiency, and thrust to power ratio. Here, the slotted APC Slow Flyer propeller blade's performance has been investigated for diverse types of airfoils with the shape and position of the slot is fixed which is a square-shaped at 62.5% of the chord length. The flow simulations are performed through three-dimensional computational fluid dynamic software (ANSYS Fluent) to determine the thrust coefficient, power coefficient, efficiency, and thrust to power ratio measured in advancing flow conditions. Findings show that the slotted propeller design composed of symmetrical, high Reynolds number, high lift airfoils can benefit the most with slots' implementation. These improvements were 19.49%, 69.13%, 53.57% and 111.06% in terms of thrust, power, efficiency and trust to power ratio respectively.
Wan Mazlina Wan Mohamed; Nirresh Prabu Ravindran; Parvathy Rajendran. A CFD Simulation on the Performance of Slotted Propeller Design for Various Airfoil Configurations. CFD Letters 2021, 13, 43 -57.
AMA StyleWan Mazlina Wan Mohamed, Nirresh Prabu Ravindran, Parvathy Rajendran. A CFD Simulation on the Performance of Slotted Propeller Design for Various Airfoil Configurations. CFD Letters. 2021; 13 (3):43-57.
Chicago/Turabian StyleWan Mazlina Wan Mohamed; Nirresh Prabu Ravindran; Parvathy Rajendran. 2021. "A CFD Simulation on the Performance of Slotted Propeller Design for Various Airfoil Configurations." CFD Letters 13, no. 3: 43-57.
A hybrid proportional double derivative and linear quadratic regulator (PD2-LQR) controller is designed for altitude (z) and attitude (roll, pitch, and yaw) control of a quadrotor vehicle. The derivation of a mathematical model of the quadrotor is formulated based on the Newton–Euler approach. An appropriate controller’s parameter must be obtained to obtain a superior control performance. Therefore, we exploit the advantages of the nature-inspired optimization algorithm called Grey Wolf Optimizer (GWO) to search for those optimal values. Hence, an improved version of GWO called IGWO is proposed and used instead of the original one. A comparative study with the conventional controllers, namely proportional derivative (PD), proportional integral derivative (PID), linear quadratic regulator (LQR), proportional linear quadratic regulator (P-LQR), proportional derivative and linear quadratic regulator (PD-LQR), PD2-LQR, and original GWO-based PD2-LQR, was undertaken to show the effectiveness of the proposed approach. An investigation of 20 different quadcopter models using the proposed hybrid controller is presented. Simulation results prove that the IGWO-based PD2-LQR controller can better track the desired reference input with shorter rise time and settling time, lower percentage overshoot, and minimal steady-state error and root mean square error (RMSE).
Mohamad Shauqee; Parvathy Rajendran; Nurulasikin Suhadis. Proportional Double Derivative Linear Quadratic Regulator Controller Using Improvised Grey Wolf Optimization Technique to Control Quadcopter. Applied Sciences 2021, 11, 2699 .
AMA StyleMohamad Shauqee, Parvathy Rajendran, Nurulasikin Suhadis. Proportional Double Derivative Linear Quadratic Regulator Controller Using Improvised Grey Wolf Optimization Technique to Control Quadcopter. Applied Sciences. 2021; 11 (6):2699.
Chicago/Turabian StyleMohamad Shauqee; Parvathy Rajendran; Nurulasikin Suhadis. 2021. "Proportional Double Derivative Linear Quadratic Regulator Controller Using Improvised Grey Wolf Optimization Technique to Control Quadcopter." Applied Sciences 11, no. 6: 2699.
In the present world, passive control finds application in various areas like flow over blunt projectiles, missiles, supersonic parallel diffusers (for cruise correction), the engine of jets, static testbeds of rockets, the ports of internal combustion engines, vernier rockets, and single expansion ramp nozzle (SERN) rockets. In this review, various passive control techniques to control the base pressure and regulate the drag force are discussed. In the study, papers ranging from subsonic, sonic, and supersonic flow are discussed. Different types of passive control management techniques like cavity, ribs, dimple, static cylinder, spikes, etc., are discussed in this review article. This study found that the passive control device can control the base pressure, resulting in an enhancement in the base pressure and reducing the base drag. Also, passive control is very efficient whenever there is a favorable pressure gradient at the nozzle exit.
Ambareen Khan; Parvathy Rajendran; Junior Sidhu. Passive Control of Base Pressure: A Review. Applied Sciences 2021, 11, 1334 .
AMA StyleAmbareen Khan, Parvathy Rajendran, Junior Sidhu. Passive Control of Base Pressure: A Review. Applied Sciences. 2021; 11 (3):1334.
Chicago/Turabian StyleAmbareen Khan; Parvathy Rajendran; Junior Sidhu. 2021. "Passive Control of Base Pressure: A Review." Applied Sciences 11, no. 3: 1334.
Various studies have been done in recent years on unmanned solar-powered aircraft for non-stop flight at a specified location or area. However, if a solar-powered unmanned aerial vehicle (UAV) can achieve a non-stop flight around the world, it may lead to the possibility of a pseudolite (i.e., pseudo-satellite) operation. These solar UAVs capable of operating as a satellite enable sustainable aviation that provides cheaper communication accessibility. Recently, we have developed a mathematical model for solar UAVs that was followed by the fabrication of a solar UAV model. Both the mathematical design model and the prototype model have been published. Thus, this work aims to determine the actual flight performance characteristics of the fabricated solar UAV. In this work, the bench and flight tests of the prototype solar and non-solar UAV model were compared in terms of aerodynamic characteristics and performance. These characteristics are determined using the flight test data and then compared with simulation data using a mathematical design model published earlier. Both accelerated and un-accelerated methods have been applied to predict the polar drag curve, and a distinct band of data obtained for both UAV prototypes. The predicted zero-lift drag coefficients were similar to the theoretical prediction in these UAVs.
Parvathy Rajendran; Howard Smith. Experimental Analysis of Small Solar Unmanned Aerial Vehicle to Predict Aerodynamic Performance. INCAS BULLETIN 2020, 12, 173 -182.
AMA StyleParvathy Rajendran, Howard Smith. Experimental Analysis of Small Solar Unmanned Aerial Vehicle to Predict Aerodynamic Performance. INCAS BULLETIN. 2020; 12 (4):173-182.
Chicago/Turabian StyleParvathy Rajendran; Howard Smith. 2020. "Experimental Analysis of Small Solar Unmanned Aerial Vehicle to Predict Aerodynamic Performance." INCAS BULLETIN 12, no. 4: 173-182.
The use of Computational Fluid Dynamics as a tool for design and analysis of aerospace systems is well established. Since the results generated by a CFD solver are numerical approximations, the solution is inherently produced with errors and uncertainties. In this paper, a simple fluid flow problem of laminar, incompressible flow past a circular cylinder at Reynolds number of 20 is allowed to be solved by the well-known finite-volume solver ANSYS Fluent. The effect of variations in mesh resolution, domain boundary location and residual criteria settings is investigated. For all the cases, finite, structured meshes of acceptable quality are used. The influence of variables on the cylinder’s drag results is analyzed and discussed. An interesting pattern in results has been observed. The study on the variation in mesh resolution showed no presence of mesh independent solution. The study on the variation of the domain distance showed that it is necessary to increase the diameter of the circle several thousand times to obtain a domain independent solution.
Aravind Seeni; Parvathy Rajendran; Mamat Hussin; Farzad Ismail. Errors and uncertainties in simulation of steady, viscous flow past a circular cylinder at Re = 20 using a systematic approach. INCAS BULLETIN 2020, 12, 203 -217.
AMA StyleAravind Seeni, Parvathy Rajendran, Mamat Hussin, Farzad Ismail. Errors and uncertainties in simulation of steady, viscous flow past a circular cylinder at Re = 20 using a systematic approach. INCAS BULLETIN. 2020; 12 (3):203-217.
Chicago/Turabian StyleAravind Seeni; Parvathy Rajendran; Mamat Hussin; Farzad Ismail. 2020. "Errors and uncertainties in simulation of steady, viscous flow past a circular cylinder at Re = 20 using a systematic approach." INCAS BULLETIN 12, no. 3: 203-217.
Passive flow control techniques are the advanced boundary surface modifiers to improve the aerodynamic performance by keeping the flow attached. The overall aim of this study is to implement semi-circular grooves over the NACA 2412 wing at various orientations, to keep the flow attached along with the relative aerodynamic performance changes of baseline and groove wing. Numerically simulation over a Low Aspect Ratio wing of order 1 with variant angle of attack, at an operating velocity of 30 m/s, and Re of 4.4 × 105 is presented. Grooves over a baseline wing disturb the flow behavior, thereby creates turbulence by producing rotating small eddies. These rotating vortices keep the flow attached for longer time by re-attaching the separated flow with enhancement in L/D characteristics. Variant of longitudinal grooves has been employed over the wingspan at different x/c location (1) near leading edge (0.2C), (2) near trailing edge (0.8C), (3) mid-span (0.5C), (4) triplet location (0.2C, 0.5C, 0.8C). The models are designed using CATIA V5R20, and ANSYS Fluent helps to simulate the flow behavior, vortex development and aerodynamic performance difference between models. From the simulation study, it is clearly understood; the baseline wing shows massive boundary flow separation on the suction side of the wing beyond 14° AOA with immediate stalling. The presence of these longitudinal grooves enhances the stalling characteristics by keeping the flow attached up to 18° AOA. In all the optimized wing models, the L/D shows at least 0.05% improvement compared to baseline wing. However, the aerodynamic characteristics show pronounced results in the case of the triplet groove wing. It proves that creating roughness over smooth wing shifts the stalling angle and also improves the lift in that region with minor turbulence drag reduction.
Samuel Merryisha; Parvathy Rajendran. Aircraft Wing Aerodynamic Efficiency Improvement Using Longitudinal Spanwise Grooves. Recent Advances in Computational Mechanics and Simulations 2020, 159 -175.
AMA StyleSamuel Merryisha, Parvathy Rajendran. Aircraft Wing Aerodynamic Efficiency Improvement Using Longitudinal Spanwise Grooves. Recent Advances in Computational Mechanics and Simulations. 2020; ():159-175.
Chicago/Turabian StyleSamuel Merryisha; Parvathy Rajendran. 2020. "Aircraft Wing Aerodynamic Efficiency Improvement Using Longitudinal Spanwise Grooves." Recent Advances in Computational Mechanics and Simulations , no. : 159-175.
In this study, a new image filter—Anisotropic Median Bilateral filter (AM-Bilateral) is proposed for image noise reduction. Unlike the Bilateral filter, AM-Bilateral filter is an iterative non-linear filter and decreases image noise continuously in every iteration. Performance evaluation of AM-Bilateral filter is done and compared with Bilateral filter, Median filter and Arithmetic Mean filter using various images with Gaussian noise. The simulation results have shown that AM-Bilateral filter outperforms other filters with higher Peak Signal to Noise Ratio (PSNR) and Structural Similarity (SSIM) on average.
Kai Yit Kok; Parvathy Rajendran. Anisotropic Median Bilateral Filtering. Recent Advances in Computational Mechanics and Simulations 2020, 151 -158.
AMA StyleKai Yit Kok, Parvathy Rajendran. Anisotropic Median Bilateral Filtering. Recent Advances in Computational Mechanics and Simulations. 2020; ():151-158.
Chicago/Turabian StyleKai Yit Kok; Parvathy Rajendran. 2020. "Anisotropic Median Bilateral Filtering." Recent Advances in Computational Mechanics and Simulations , no. : 151-158.
The aerodynamic performance of a propeller is characterized by the thrust produced, torque and efficiency. In this paper, novel blade shapes are tested using the technique Computational Fluid Dynamics (CFD). The blade shapes are based on a passive slotted design in which slots are present on the suction side i.e. on the upstream front side of the blade. Two slotted design models are tested using the commercial CFD solver ANSYS Fluent. The slotted designs are identical in terms of slot geometry (0.1 mm width, 0.2 mm depth) but differ in the location of slot along chord from leading edge (0.206c and 0.382c). In order to test the modified designs, a validation study of the baseline model of a propeller is conducted. Then slotted designs comprising two models are tested and compared to baseline design. The propeller model considered is the APC10x7 Slow Flyer and the Reynolds number of flow analyzed is approximately 68,500 (estimated at 75% radial distance) The results showed that the presence of slots have altered the performance. The presence of slots has reduced the thrust performance for the entire operational range of advance ratios. However, the power performance has increased due to decrease in torque or rotational resistance of the propeller. The efficiency is thereby increased for one model for a specific range of advance ratios. In the case of another model, for most advance ratios the efficiency was found to be decreased.
Aravind Seeni; Parvathy Rajendran. CFD Analysis of a Novel Propeller Design Operating at Low Reynolds Number. Recent Advances in Computational Mechanics and Simulations 2020, 139 -150.
AMA StyleAravind Seeni, Parvathy Rajendran. CFD Analysis of a Novel Propeller Design Operating at Low Reynolds Number. Recent Advances in Computational Mechanics and Simulations. 2020; ():139-150.
Chicago/Turabian StyleAravind Seeni; Parvathy Rajendran. 2020. "CFD Analysis of a Novel Propeller Design Operating at Low Reynolds Number." Recent Advances in Computational Mechanics and Simulations , no. : 139-150.
In this paper, CFD is used to perform analyses of 3 different airfoils at varied angles of attack. The objective is to determine a suitable CFD model and find a single validated simulation setting applicable for different airfoils. The pressure coefficient around an airfoil is analyzed. A single Reynolds number condition is assigned for testing of each airfoil over different angles of attack. The CFD results are compared with experimental and XFOIL data. The solver used is the commercially available ANSYS v16.0 CFX. From this study the following results are derived: It is found that the simulation results closely match experimental results at Reynolds number in the range of 3 million. At low Reynolds number, the CFD approach struggles to reach the higher values of pressure coefficient achieved experimentally. It is also found that XFOIL provided better results compared to CFD and also converged at a faster rate. The above results are discussed in this paper.
Aravind Seeni; Parvathy Rajendran. Analysis of Pressure Coefficient Around Three Airfoils Operating at Different Reynolds Number Using CFD and XFOIL. Recent Advances in Computational Mechanics and Simulations 2020, 127 -137.
AMA StyleAravind Seeni, Parvathy Rajendran. Analysis of Pressure Coefficient Around Three Airfoils Operating at Different Reynolds Number Using CFD and XFOIL. Recent Advances in Computational Mechanics and Simulations. 2020; ():127-137.
Chicago/Turabian StyleAravind Seeni; Parvathy Rajendran. 2020. "Analysis of Pressure Coefficient Around Three Airfoils Operating at Different Reynolds Number Using CFD and XFOIL." Recent Advances in Computational Mechanics and Simulations , no. : 127-137.
This paper presents an enhanced particle swarm optimization (PSO) for the path planning of unmanned aerial vehicles (UAVs). An evolutionary algorithm such as PSO is costly because every application requires different parameter settings to maximize the performance of the analyzed parameters. People generally use the trial-and-error method or refer to the recommended setting from general problems. The former is time consuming, while the latter is usually not the optimum setting for various specific applications. Hence, this study focuses on analyzing the impact of input parameters on the PSO performance in UAV path planning using various complex terrain maps with adequate repetitions to solve the tuning issue. Results show that inertial weight parameter is insignificant, and a 1.4 acceleration coefficient is optimum for UAV path planning. In addition, the population size between 40 and 60 seems to be the optimum setting based on the case studies.
Kai Yit Kok; Parvathy Rajendran. Enhanced Particle Swarm Optimization for Path Planning of Unmanned Aerial Vehicles. ECTI Transactions on Computer and Information Technology (ECTI-CIT) 2020, 14, 67 -78.
AMA StyleKai Yit Kok, Parvathy Rajendran. Enhanced Particle Swarm Optimization for Path Planning of Unmanned Aerial Vehicles. ECTI Transactions on Computer and Information Technology (ECTI-CIT). 2020; 14 (1):67-78.
Chicago/Turabian StyleKai Yit Kok; Parvathy Rajendran. 2020. "Enhanced Particle Swarm Optimization for Path Planning of Unmanned Aerial Vehicles." ECTI Transactions on Computer and Information Technology (ECTI-CIT) 14, no. 1: 67-78.
A new image filter, Spot & Adjust filter, is proposed in this paper in order to remove noise from an image. It spots out the error pixels and recovers the intensity value using the absolute intensity difference and the average value of the local region. The performance of this filter is analyzed using seven types of image noise samples, which are Gaussian, Gamma, Rayleigh, Poisson, Salt and Pepper, Speckle and Uniform noise. Six types of image filters are analyzed in this work, including the Median, Minimum, Maximum, Arithmetic Mean, Geometric Mean, and Harmonic Mean filters. These image filters' performance is compared with the newly proposed filter in terms of Peak Signal to Noise Ratio (PSNR). The results have shown that the Spot & Adjust filter has excellent performance, especially in tackling Poisson noise and Salt & Pepper noise. Copyright © 2020 Praise Worthy Prize - All rights reserved.
Kai Yit Kok; Parvathy Rajendran; Aiffah Mohd Ali. Spot and Adjust Filter: a New Image Filter for Image Enhancement and Noise Reduction. International Journal on Engineering Applications (IREA) 2020, 8, 71 .
AMA StyleKai Yit Kok, Parvathy Rajendran, Aiffah Mohd Ali. Spot and Adjust Filter: a New Image Filter for Image Enhancement and Noise Reduction. International Journal on Engineering Applications (IREA). 2020; 8 (2):71.
Chicago/Turabian StyleKai Yit Kok; Parvathy Rajendran; Aiffah Mohd Ali. 2020. "Spot and Adjust Filter: a New Image Filter for Image Enhancement and Noise Reduction." International Journal on Engineering Applications (IREA) 8, no. 2: 71.
Kernelized Correlation Filters Parameters Optimization for Enhanced Visual Tracking
Chor Keat Ong; Parvathy Rajendran. Kernelized Correlation Filters Parameters Optimization for Enhanced Visual Tracking. Journal of Engineering and Applied Sciences 2019, 14, 293 -307.
AMA StyleChor Keat Ong, Parvathy Rajendran. Kernelized Correlation Filters Parameters Optimization for Enhanced Visual Tracking. Journal of Engineering and Applied Sciences. 2019; 14 (1):293-307.
Chicago/Turabian StyleChor Keat Ong; Parvathy Rajendran. 2019. "Kernelized Correlation Filters Parameters Optimization for Enhanced Visual Tracking." Journal of Engineering and Applied Sciences 14, no. 1: 293-307.
This paper presents a survey on existing stereo vision algorithms. The existing stereo vision algorithms are discussed in terms of concept, performance and related improvements. Also, a brief analysis of performance comparison among existing stereo vision algorithms is presented. Moreover, available improvements and solutions for stereo vision challenges such as computational complexity, occlusion, radiometric distortion, depth discontinuity and textureless region are reviewed.
Kai Yit Kok; Parvathy Rajendran. A Review on Stereo Vision Algorithm: Challenges and Solutions. ECTI Transactions on Computer and Information Technology (ECTI-CIT) 2019, 13, 112 -128.
AMA StyleKai Yit Kok, Parvathy Rajendran. A Review on Stereo Vision Algorithm: Challenges and Solutions. ECTI Transactions on Computer and Information Technology (ECTI-CIT). 2019; 13 (2):112-128.
Chicago/Turabian StyleKai Yit Kok; Parvathy Rajendran. 2019. "A Review on Stereo Vision Algorithm: Challenges and Solutions." ECTI Transactions on Computer and Information Technology (ECTI-CIT) 13, no. 2: 112-128.
Validation of the sectional airfoil performance is necessary to test a propeller. This study presents a numerical validation of the computational fluid dynamics (CFD) method for testing a symmetric NACA airfoil called NACA 0009. An ultra-low Reynolds number of 20000 is assumed and investigated. The implementation is performed using a commercial CFD solver ANSYS Fluent. The obtained results are compared with experimental data obtained from literature. A coarse grid is adopted as meshing technique and a realizable k-ε turbulence model, which has provided the best results, is assumed. Results show favourable prediction for most of the considered angles of attack. Thus, an overall reliable model has been developed. Copyright © 2019 Praise Worthy Prize - All rights reserved.
Aravind Seeni; Parvathy Rajendran. Numerical Validation of NACA 0009 Airfoil in Ultra-Low Reynolds Number Flows. International Review of Aerospace Engineering (IREASE) 2019, 12, 83 .
AMA StyleAravind Seeni, Parvathy Rajendran. Numerical Validation of NACA 0009 Airfoil in Ultra-Low Reynolds Number Flows. International Review of Aerospace Engineering (IREASE). 2019; 12 (2):83.
Chicago/Turabian StyleAravind Seeni; Parvathy Rajendran. 2019. "Numerical Validation of NACA 0009 Airfoil in Ultra-Low Reynolds Number Flows." International Review of Aerospace Engineering (IREASE) 12, no. 2: 83.
The need to develop aerodynamically and structurally efficient aircraft for a variety of purposes or missions has motivated aircraft designers to seek inspiration from nature and mimic the features of avian flight. The goal is to develop a promising morphing structure based on piezoelectric smart material technology to ensure structural integrity, reduced weight penalty, and enhanced performance. The embedding of smart piezoelectric actuators within an adaptive structure provides a great opportunity to affiliate the efficiency of avian flight with a smart adaptive wing. Piezoelectric actuators for these adaptive structures are constrained to have a high-energy density, an ease of restraint, a variable stiffness, and a high proficiency for carrying substantial strains. Our study enumerates recent trends in the development of piezoelectric smart materials and actuators and their applications to morphing aircraft. These advancements will motivate the development of new morphing techniques and aid in maximizing the potential of shape shifting. Copyright © 2019 Praise Worthy Prize - All rights reserved.
Musavir Bashir; Parvathy Rajendran. Recent Trends in Piezoelectric Smart Materials and Its Actuators for Morphing Aircraft Development. International Review of Mechanical Engineering (IREME) 2019, 13, 117 .
AMA StyleMusavir Bashir, Parvathy Rajendran. Recent Trends in Piezoelectric Smart Materials and Its Actuators for Morphing Aircraft Development. International Review of Mechanical Engineering (IREME). 2019; 13 (2):117.
Chicago/Turabian StyleMusavir Bashir; Parvathy Rajendran. 2019. "Recent Trends in Piezoelectric Smart Materials and Its Actuators for Morphing Aircraft Development." International Review of Mechanical Engineering (IREME) 13, no. 2: 117.