Engineering

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AERODYNAMIC ANALYSIS AND PERFORMANCE STUDY OF MODIFIED HYBRID WIND TURBINE WITH HELICAL SAVONIUS AND H-TYPE DARRIEUS ROTOR
(I.O.E, 2024-04) DUWADI, BIRAT; SHRESTHA, SAMIR; DHAKAL, SUJAN; WAGLE, SURAJ; Motra, Laxman
This report aims to explore the potential of combining the Darrieus and Savonius vertical axis wind turbine (VAWT) designs to create a more efficient and versatile renewable energy solution. The Darrieus VAWT is known for its high efficiency in capturing wind energy, while the Savonius VAWT exhibits excellent self-starting capabilities and performs well in low wind conditions. By combining these two designs, we aim to leverage their respective advantages and overcome their individual limitations. The present report introduces a CFD analysis of a proposed hybrid VAWT using ANSYS Fluent and experimental analysis. Straight blade with airfoil profile S1046 was used for darrieus rotor. The hybrid rotor has a helical Savonius rotor with 3 Darrieus blades. The performance study of hybrid rotor at different radius ratios are carried out and highest power coefficient is achieved at 0.43 radius ratio. It is found that radius ratio greatly affects the performance of the turbine. The larger the diameter of Savonius rotor, more is the interaction of Savonius and Darrieus blades resulting loss in performance. The final optimized design is fabricated and experimentally tested.
Design and Fabrication of a Phase Change Material (PCM) Based Heat Storage Setup
(I.O.E, 2024-04-12) Bhattarai, Gaurav; Kattel, Gaurav et al; Jha, Navin Kumar
This report outlines a significant project focused on developing and testing two different methods to store heat using special materials called phase change materials (PCMs) within heat exchangers. Initially, the project started with basic designs for heat exchangers such as double pipe and shell & tube configurations. As the project progressed, advanced features like radial fins and PCM integration were incorporated to improve heat exchange efficiency and storage capacity. Using ANSYS Fluent, detailed computational fluid dynamics (CFD) and thermal simulations were conducted to understand how heat transfers within these systems. These simulations provided valuable insights into heat transfer dynamics, guiding the refinement of designs. Subsequently, one of the shell & tube PCM heat storage setups was fabricated and tested to validate theoretical models. The experimental results closely matched predictions, confirming the effectiveness of the design approach.
DESIGN AND FABRICATION OF ELASTIC-DRIVEN UNMANNED AERIAL VEHICLE(UAV) LAUNCHER
(I.O.E, 2024-04-12) B.K, Avinash; Limbu, Poonam; Giri, Manush; Poudel, Sudarshan; Neupane, Sanjay
Unmanned Aerial Vehicles (UAVs) have proven indispensable in various applications, from surveillance to environmental monitoring. UAV deployment efficiency is critical for fast reaction and better mission capabilities. This project offers a Elastic Driven UAV Launcher, which is intended to provide a reliable and fast launch mechanism for UAVs in a variety of settings. To push UAVs into the air, the launcher uses a Elastic-based technology, eliminating the need for standard propulsion techniques such as gas or electric motors. This breakthrough promises to minimize launch complexity, and operating costs. The system’s architecture has an elastic mechanism capable of effectively storing and releasing energy. The launcher may be adapted to different UAV sizes with weights up to 10kg, ensuring compatibility with a wide range of UAV types. Different launch tests for load of 2.6kg and 10 degrees launching angle resulted in launch speed of 6.25m/s and error of 65.8% using 3 elastic bands whereas launch speed of 3.23 m/s and error of 46.8% using 2 elastic bands respectively.
Design, Fabrication, and Experimental Analysis of Tiltrotor Mechanism
(I.O.E, 2024-03) Luitel, Kshitij; Koirala, Kushal Sharma; Gurung, Monika; Dahal, Ujjwal; Karki, Ashish
This paper presents the design and synthesis of a tilt-rotor mechanism for a hybrid UAV that can perform vertical takeoff and landing (VTOL) and fixed-wing flight. The tilt-rotor mechanism allows the orientation of the propulsion system to change from vertical to horizontal or vice versa, enabling the UAV to fly like a helicopter or an airplane. The paper describes the design, mathematical modeling, structural analysis, and fabrication of the mechanism, as well as the design and testing of a test bench and a control system. The paper also evaluates the performance of the mechanism and the system on a bi-copter UAV model and discusses the challenges, limitations, and future enhancements of the project. The paper concludes that the tilt-rotor mechanism is a promising solution for hybrid UAVs that can combine the advantages of both rotorcraft and fixed-wing UAVs.
DEVELOPMENT AND TESTING OF AUTONOMOUS FIXED-WING UAV FOR SAFE MEDICAL PAYLOAD DELIVERY
(I.O.E, 2024-03-10) Chapagai, Aayush; Karki, Bhimraj; Thapa, Dakshesh; Sapkota, Niyat; Karki, Ashish
This project endeavors to develop a cost-effective and efficient Unmanned Aerial System (UAS) designed for transporting medical supplies to remote and challenging locations. The UAS, a fixed-wing aircraft, incorporates a parachute system to ensure the secure and safe delivery of medical cargo. The design process involves optimizing aerodynamic characteristics, flight dynamics, payload capacity, and the parachute deployment mechanism to ensure successful deliveries, especially across difficult terrains.The major objective of the project is to ensure a quality built of a fixed wing UAV which can effortlessly deliver the medical goods to the remote location of the Solukhumbu district in time of crisis and need. The Terrain of Nepal itself being quite complex and difficulty for mode of transportation to reach the remote location make use of UAV like Aid-Plane more viable. The prototype underdevelopment later can be used not just for medical sectors but also facilitate other major sectors and regions of Nepal
DEVELOPMENT AND TESTING OF AUTONOMOUS MOBILE ROBOT FOR MATERIAL HANDLING
(I.O.E, 2024-04) Panta, Nirmal Prasad; Shrestha, Pawan; Panta, Prince; Basnet, Saki; Adhikari, Surya Prasad
The adoption of autonomous mobile robots (AMRs) for material handling has witnessed significant growth in various industries, including manufacturing, healthcare, and the service sector. To stay competitive in this era of automation, businesses are increasingly transitioning from human labor to AMRs for efficient transportation and material handling. This project involves developing and testing AMR that utilizes Simultaneous Localization and Mapping (SLAM) and Nav2 (Navigation2) for precise navigation and Computer Vision (CV) for enhanced material handling capabilities. In the first phase, design and development of the mobile robot is done. The second phase involves incorporating SLAM and Nav2 for autonomous mobility of the robot, enabling it to navigate complex environments with accuracy and efficiency and finally, in the third phase, OpenCV is integrated into the autonomous mobile robot for ArUco tag detection for material handling operations. Therefore, in these three phases, we have developed and tested an AMR for material handling purpose using ROS2, SLAM, Nav2 and OpenCV. The process used in this project can be a clear guideline on completing similar projects related to autonomous mobile robots using ROS2 in various areas ranging from manufacturing industries to service industries.
Development of an An Autonomous Unmanned Aerial System for Radio Frequency Source Localization
(I.O.E, 2024-03) Gupta, Nirajan Prasad; Dahal, Prithak; Acharya, Priyank Raj; B.K., Swastik Om; Thapa, Arun Kumar
Radio-based direction finding or radio-based localization is a new and growing field of study for an Unmanned Aerial System. While this concept had been used in manned aircrafts previously, the ‘autonomous’ process in UAS makes it an interesting area of research. Although there are many approaches to localization in outdoor environments, the proposed project primarily aims to utilize both the deterministic and probabilistic approach to localize the radio source in an outdoor environment with an autonomous drone, utilising a moxon antenna and an omni-directional antenna.
Experimental Analysis on Vapour Compression Refrigeration System
(I.O.E, 2024-04) Shrestha, Jeena; Thapa, Niraj; Pradhan, Rejisha; Baniya, Sujit Sah; Amatya, Vishwo Prasad
Vapour Compression Refrigeration system (VCRs) has been extensively used in Refrigeration and HVAC sectors due to its beneficial characteristics like higher COP and Refrigerating Effect. However, these sectors and consequently VCRs contribute to a substantial and rapidly increasing global energy consumption which has raised huge concerns. This project aimed to experimentally analyse the vapour compression refrigeration system and compare performance of the system with and without heat addition. It was conducted by fabricating a VCR unit and adding extra heat to the unit before and after the compression process. The COP of the system increased by 46.07% when heat was added before compressor while the current consumption of the compressor decreased by 12.07%. However, COP of the system decreased by 22.7% when heat was added to the system after compressor with 32.6% increase in current consumption.
EXPERIMENTAL INVESTIGATION OF FLOW OVER A CYLINDER AND WING WITH VORTEX GENERATORS USING PIV
(I.O.E, 2024-03) Devkota, Kshitish Chandra; Mishra, Praphul; Adhikari, Sandip; Banjade, Shreeju; Darlami, Kamal
Particle Image Velocimetry (PIV) is a non intrusive flow measurement technique used for qualitative and quantitative analysis of flow dynamics. In this study, PIV is employed to investigate flow behaviour around a circular cylinder and a wing, with and without vortex generators (VGs). The research pursues dual objectives: to characterize the PIV setup using the Strouhal number (a dimensionless parameter) and to analyze flow characteristics, particularly focusing on stall conditions. Systematically, a linear actuation mechanism is developed to facilitate experimentation on both models. Image processing, conducted in PIVLab alongside the development of necessary code written in MATLAB, are incorporated for detailed analysis, with time-dependent signals transformed into the frequency domain using Fast Fourier Transform (FFT) for comprehensive evaluation. The characterization of existing PIV setup was done through three sets of experimental data using strouhal number for analysis of flow around circular cylinder. The strouhal number obtained are 0.1897, 0.1952 and 0.1952 with 3.6777 %, 0.9137 % and 0.9137 % errors respectively. Velocity field and vorticity contours were studied for the aerodynamic flow analysis of baseline wing and wing with VG at the 15 degree angle of attack. The obtained Strouhal number for wing and wing with VGs are 0.1381 and 0.1571 respectively. The comparison concludes that vortex generators energize the boundary layer above the wing and delay the flow separation
MODEL PREDICTIVE CONTROL-BASED OPTIMAL TRAJECTORY TRACKING IN AUTONOMOUS QUADROTOR SYSTEM
(I.O.E, 2024-03) Simkhada, Dipesh; Bhatta, Hemant; Karki, Krishna Bahadur; Thapa, Prasanna Pratap; Luitel, Mahesh Chandra
Optimal trajectory tracking through nonlinear optimization is a computational process that aims to track the reference path for a system, considering the dynamics and objectives of system along with the constraints that are provided. Among current approaches in trajectory tracking formulation as an optimization problem, this paper describes Model Predictive Control( MPC), an approach that provides a continually evolving optimized trajectory tracking system that also respects system dynamics and constraints. The project showcases both the numerical simulation for the MPC implemented for reference trajectory tracking followed by an implementation on the actual quadcopter. However, in the actual hardware implementation flight test have been conducted in the quadrotor where only the attitude has been controlled in the PX4 firmware directly using Model Predictive Control. In this paper, the MPC-based control technique is used for trajectory tracking of the quadrotor model in different types of trajectories. For numerical simulation, non linear model has been developed and analyzed using the Finite-length time horizon control referred to as Model Predictive Control whereas, for SITL(Software-in-The-Loop) simulation, linear model of MPC have been used. For the flight test, to achieve efficient computational cost for the Pixhawk Flight Controller, the linear model has been implemented to analyze the attitude control shown by the quadrotor system.
NUMERICAL SIMULATION OF HYPERSONIC FLUID-STRUCTURE INTERACTION ON CANTILEVER PLATE WITH OSCILLATING SHOCK IMPINGEMENT
(I.O.E, 2024-03) Paudel, Prabin; Shahi, Sanskar Chandra; Pandey, Sarthak; Kharel, Sashakta; Bhattarai, Sudip
When an entity surpasses the velocity of sound, it undergoes a process where it compresses the air molecules preceding it, resulting in the formation of a region characterized by heightened pressure called a shock wave. When this shock wave encounters a physical framework, the framework becomes exposed to a load of pressure, potentially leading to structural deformation. These scenarios, wherein the interaction between a fluid medium and structures is involved, are effectively tackled through the discipline of fluid-structure interaction (FSI). In the case of hypersonic vehicles, shock waves impact the structures of control surfaces, thereby instigating fluid-structure interaction within said structures. The scope of this study is to carry out a numerical simulation of Hypersonic Fluid-Structure Interaction on a Cantilever plate with oscillating shock impingement location using the UNSW Canberra’s HyMAX benchmark test case. The numerical simulation is carried out in two approaches i.e. Low Fidelity Modeling (LFM) and High Fidelity Modeling (HFM). In LFM, the problem is modeled based on shockwave Expansion Theory , Piston Theory and Euler Bernoulli Model. Whereas in HFM, the problem is solved by coupling a fluid solver, OpenFOAM, with a structural solver, CalculiX, via a coupling library, preCICE. The shock-generating wedge was given a predefined oscillating rotating motion with a frequency of 42 Hz.

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