| Over the years, UAV technology is growing very fast, our country and foreigncountry both pay close attention to UAV technology. Small UAV has many features,such as small size, low cost, easy to use, etc, and play a significant role in policing,firefighting, and surveillance of pipelines as well.Based on the research principle flight control system, this paper make thetraditional PID control theory combine with the inertial navigation system and globalpositioning system, so that the running of the UAV is more stable and the positioningis more precise. A series of STM32microcontrollers chips, inertial attitude sensor,GPS receiver and datalink radio modem have been used as basic framework to designand implement the UAV flight control system. Historically, fixedwing UAV aircraftused a set of6orthogonal infrared temperature sensors to estimate the orientation ofthe aircraft relative to the warm earth and the cold sky. Even though the IR systemprovides a robust and absolute attitude estimate that is immune to vibration anddisorienting launches, using inertial attitude sensor to measure attitude of UAV iseasier to operate, and the results are more accurate. Using bi-directional datalink fortelemetry mode, The telemetry part of the link (from aircraft to ground) is used toobtain status information about the UAV to aid an operator and monitor missionprogress, as well as provide some payload data. The datalink or telecontrol part of thelink (from ground to aircraft) is used to send commands to the aircraft and interactwith a payload. In different region of globe world, the magnetic variation is different,we correct the magnetic variation and inertial attitude sensor to ensure the measuredUAV’s attitude parameters accurately.In addition, this paper also introduce the required hardwares to build flightcontrol system in detail, and analysis the involved interface circuit. The final resultsshows that each module of the UAV flight control system can work normally, andachieve the desired effect. |
