Completed Projects

[P6.2]. Waypoint Navigation with High-Fidelity Flight Simulation Model.

IMG_2309.MOV

[P6.1]. Waypoint Navigation for Medium Altitude Long Endurance (MALE) Unmanned Aircraft with an INDI Controller.   

[P5]. Optimal Climb Trajectory Generation for Various Flight Altitude Profile and Aircraft Configuration   

[P4]. Flight Dynamics and Control of Tricopter VTOL and Tilt Rotor Transition to Fixed Wing

[P3].Incremental Nonlinear Dynamics Inversion (INDI) Controller Design for Autonomous  Landing OF Aircraft  (ALOA)


[P2]. Development of Aircraft Autopilot for Medium Altitude Long Endurance (MALE)







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