Projects
Flight Control System of a Drone
The following paper explores mathematical dynamic models of the QuanserTM Qball-X4 quadrotor helicopter and goes on to present the conventional PID control algorithm used in developing an autopilot system. The system is modelled and simulated using MATLAB Simulink and results of the Qball-X4 responses are discussed. Future work and improvements to the control techniques implemented are then suggested.
CFD analysis of VKI Blade
Numerical simulation has an important role to play in the modern designing process to increase the design efficiency. Finite difference and finite volume methods are particularly used for the application of Computational Fluid Dynamics [CFD].Objective of this project is to run a 3-dimensional CFD simulation of a VKI blade to obtain turbine perform parameters using Ansys CFX and Post processing.
Estimation of NACA 4421 Aerodynamic Properties
As part of our project, we are attempting to find the aerodynamic properties of a NACA 4421 airfoil using preliminary approximation methods such as thin airfoil theory, vortex panel method and finite wing theory. We conducted these methods to evaluate and compare the aerodynamic properties of the airfoil.
Review on Sensor less load angle control of stepper Motor
In this project, a load angle estimation algorithm, solely based on voltage and current measurements, is used to provide the necessary feedback without using a mechanical position sensor. Also, a closed-loop load angle controller which optimizes the current level based on the estimated load angle is introduced. A linear model is proposed and is used to tune a PI load angle controller. The controller reduces the current level to obtain the optimal load angle but does not change the way stepping motors are driven. We with reference of this paper try to replicate the load angle estimator with a similar approach yet simpler than the one mentioned in the paper.
CFD Analysis of Converging Diverging Nozzle
In this project, we will be presented the results obtained for theoretical 1-dimension calculation of isentropic, normal shock and oblique shock properties in a converging diverging nozzle. The results will be evaluated in CFD with different cases.
Plasma Turbine
Plasma Propulsion engines tend to be designed to work in a vacuum or the low pressures, where they would need to carry a gas supply. But, a new design has been tested one that can operate on air at a pressure of one atmosphere. These jets of plasma can reach speeds of up to 20 km/s. A rapid stream of nanosecond-long electric discharges was used to fire up the propulsion mixture. This idea has the potential to greatly extend the range of any aircraft and lower the operational cost. This report explores the present and future of this technology.
