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.

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.

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.

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.