Completed Projects
[P6.2]. Waypoint Navigation with High-Fidelity Flight Simulation Model.
This project presents waypoint navigation with a high-fidelity flight simulation model.
Applicable for both multirotor as well as fixed wing aircraft .
The implemented Carrot Chasing algorithm is tested against the linear (PID) as well as nonlinear (INDI) controller.
For a predefined intended path, the solution is made available for various aircraft configurations.
![](https://www.google.com/images/icons/product/drive-32.png)
[P6.1]. Waypoint Navigation for Medium Altitude Long Endurance (MALE) Unmanned Aircraft with an INDI Controller.
This project presents waypoint navigation for MALE aircraft.
The INDI controller is designed and implemented to achieve the defined waypoint.
Applicable for fixed wing aircraft .
[P5]. Optimal Climb Trajectory Generation for Various Flight Altitude Profile and Aircraft Configuration
This project presents a novel approach for generating the best possible climb trajectory that ensures a fuel- and time-efficient climbing flight.
The flight simulation model is capable of incorporating different configurations, available fuel, and different engines.
Based on weight class, altitude profile, available fuel, and selected engine. This simulation framework is able to compute the endurance of the entire altitude profile.
Whether or not the flight is possible with the given configuration. The model that was developed will reveal.
The solution made available if the flight is NOT possible using this model.
[P4]. Flight Dynamics and Control of Tricopter VTOL and Tilt Rotor Transition to Fixed Wing
The modelling and simulation of a tricopter with fixed wing aircraft for the design of VTOL (Vertical Take-off and Landing) with this configuration is presented.
The flight dynamic model for the try copter is developed and integrated into the typical fixed wing flight dynamic model.
The forward and backward transition is performed by tilting the trycopter rotor.
A surveillance small unmanned aircraft is being considered to show the proposed approach. For the VTOL phase, proportional, integral, and derivative control are used, whereas incremental nonlinear dynamic inversion is used for the forward phase.
[P3].Incremental Nonlinear Dynamics Inversion (INDI) Controller Design for Autonomous Landing OF Aircraft (ALOA)
INDI Control Law is designed.
Position and attitude control for ALOA with ground effect is demonstrated.
Flare trajectory is designed.
ALOA simulation is performed with ground contact model and wind effect on landing trajectory.
[P2]. Development of Aircraft Autopilot for Medium Altitude Long Endurance (MALE)
Take-off, Climb, Cruise, Loiter, Descent and Landing control law design using classical control theory
Roll hold, pitch hold, heading hold, altitude hold, and speed hold; control loop performance has been demonstrated.
Autonomous flight simulation for the full flight envelope is performed.
Control law is analyzed with external disturbance (Wind, Gust, and turbulence) rejection.
Control law stability is verified at desired trim points.
Aircraft Design Projects
[P1]. UAVs Design
Note: Several aircraft with weight classes in different configurations (fixed wing, VTOL etc.,) ranging from 1.5 kg to 1500 kg have been designed. Below are two examples of aircraft along with their technical specifications. The rest of the aircraft and additional technical information on the aircraft are available upon request.
Technical Specification UAV_25
UAV Type: Fixed wing (25 kg)
Engine: DA70 with EFI
Fuel weight: 5 kg
Wing span: 4.34 m (Rectangular semi span 0.774 m
Tapered 1.446 m)
Wing area: 1.57 m^2
Stall speed: 14.0 m/s at 0km and 18.05 m/s at 5 km altitude
Cruise speed: 18.2 m/s at 0km and 23.47 m/s at 5 km
Rate of climb at 0 and 5 km : 8.2 m/s and 7.9 m/s
(@ 70% throttle setting)
Wing loading: 15.92 kg/m^2
Technical Specification UAV_22
UAV Type: Fixed wing (22 kg)
Engine: 3W-28iCS
Fuel weight: 6 kg
Endurance: >25 hrs
Wing span: 3 m
Wing area: 0.75 m^2
Stall speed: 18.3 m/s at 0km and 23.6 m/s at 5 km altitude
Cruise speed: 23.7 m/s at 0km and 30.70 m/s at 5 km
Rate of climb at 0 and 5 km : 6.9 m/s and 6.7 m/s
(@ 70% throttle setting)
Wing loading: 29.33 kg/m^2