Design Of An Electromagnetical Flight Control Actuation System For Medium-sized Uav

Recent regional wars and anti-terrorist warfare have witnessed the frequent exposures of military Unmanned Aerial Vehicles(UAVs), among which Medium Altitude Long Endurance(MALE) UAV, as its name indicated, plays a vital role in recon-strike combined missions. Thanks to the development of UAV towards more autonomous and more intelligent ones, digital fly-by-wire Flight Control System(FCS)has become one of the standard applications to heavy-to-medium-weight UAVs.Further, since their rise in 1980 s, the concepts of More Electric Aircraft(MEA)/All Electric Aircraft(AEA) have been proved to be more advanced in terms of battlefield survivability, system efficiency, maintainability, and reliability. As one of the key technology in MEA/AEA system, power-by-wire flight control actuation system has achieved a new progress, like Electro-hydrostatic Actuator(EHA) and ElectroMechanical Actuators(EMA). EHA and EMA are different in composition, and therefore vary in strength and weakness. In recent decades, EMA has been discussed more due to its potentials to be applied to AEA. With increasing safety and reliability,EMA starts replacing the old actuators in main FCS actuating system.A design of EMA actuation system applied on medium and small UAVs was introduced in this paper. Starting from the development and application of Aircraft and Flight Control, the development and skill features of recent fly-by-wire Flight Control System(FCS), power-by-wire actuation system were particularly explained, and examples for all kind of flight control actuating technology were cite. Based on the background and contrastive analysis, architecture of the flight control system for an innominate UAV was set down. The structure of flight actuation system was optimized based on flight control surface configuration, considering the precondition of the whole airframe system. EMAs were chosen as the driven components for flight control system on consideration of the limited power and installation space on the UAV.EMA Design includes hardware design, safety and reliability analysis. Hardware design takes “From top to bottom” method. Through EMA structure analysis, critical components calculating, the function of actuators could full fill the function and specification technology requirements. The safety and stability analysis made the target more clear, and ensure the flight control actuation system reach the design requirement of a modern aircraft. Based on aileron, the work of control loop simulation, practicalitytest and data analysis made the whole design complete and efficient.In this project, the distribute FCS actuation system with EMAs has the feature of digital and modular, which had efficiently improved the system stability and adaptability on the other platforms.