Aircraft Free Flight Simulation in a Wind Tunnel

Abstract

The Unmanned Ariel Vehicle Model is Mounted in the Wind Tunnel. where its Longitudinal Motion of Electric Propeller was Developed and Simulated as a Free Aircraft Flight. the Numerical Values of the Aerodynamic Stability and Control Derivatives are Evaluated via the Digital Tornado Algorithm. this Evaluation is Carried out Based on the Geometric Parameters of the Airplane, Aircraft Center of Gravity and Mass Moment of Inertia. the Stability and Response of the Linearized Longitudinal Model of the Considered Aircraft are Tested and Investigated. the Onboard Computer is Implemented Based on a Microcontroller Pic16f877a, where the Pitch Angle and Speed of the Considered Free Flight Vehicle are Read Respectively by an Gyroscope and Pressure Sensors. and the Microcontroller Read these Signals via Analog to Digital Converter which are in Turns as a Serial Digital Data by Using of Universal Synchronous Asynchronous Receive Transmit. Apply the Personal Computer to Receive the Serial Signal through the PC RS232 Standard as Serial Data. where in the PC, the Visual Basic Algorithm is Written as well in Order to Display and Plot the Pitch Angle Airspeed Responses on the Screen. Finally, the Experimental Results of Aircraft Free Flight in Real Time are Obtained by Carrying out the Simulation in the Wind Tunnel.