Simulation and Optimization of Integrated Guidance and Control System in Small Aircrafts

one of the main concerns in the present navigation systems is their single-based. Navigation rely on one system will be very insecure and subjected to very high probability of errors. Therefore, having a navigation aid system or the use of two sensors at the same time can be the best way to reduce this very serious risk. In this research, simulation and software design to optimize movement and autopilot of small aircraft has been considered. At first, dynamic modelling of the aircraft with integrated inertial navigation and extended Kalman filter is developed. To obtain reliable results, the position and inertia sensors as well as actuator errors are modeled in simulation of the aircraft. Furthermore, to get closer to the reality, weather conditions for different wind speed also simulated and added to the PID control system. In order to increase the accuracy of the control system and ensure the precistion of performance, all commands and algorithms of the control system have been designed in three level and tested in two stages of open-loop and closed-loop simulations. The closeness of simulation results with of experimental tests indicates the correct choice of control algorithms, suitable modeling of components and precision simulation of the system.In this article, design and optimization of the nonlinear autopilot software of Desert Hawk hand launch UAV is reviewed using GPS and INS systems. To obtain more realistic results, the sensors and actuators of the autopilot have been modeled and installed in the control system. According to the complexity of the flight algorithm, PID controller is used in the series circuit. The comparison between the results of this method and experimental results approves the appropriate design and simulation of the system components.