Research On Realization Technique For Fly-by-light System

Compare to the fly-by-wire system, the fly-by-light system has an ability of anti-electromagneticinterference, large transmission capacity, small volume and light weight. So it is the futuredevelopment trend and research focus in the field of flight control system. In this paper, a carriertakeoff and landing hardware-in-loop simulation platform is developed to verify the fly-by-lightsystem. The key technique of the fly-by-light, such as flight control computer, fly-by-light/power-by-wire actuator, modern flight control law, and redundancy technology with fault diagnosis, isdesigned and verified. The research achievement of this paper has a very important application valuefor the realization of fly-by-light system.The core research achievements of this thesis summarized as follows:Firstly, the solutions of development and verification platform for the fly-by-light system areproposed based on carrier takeoff and landing system, to meet the requirement of realization of thefly-by-light system. And the function and Implementation technology of the main components isanalysed and designed. This platform with features of multiple functions, modular and opening is veryuseful for the research in related fields.Secondly, in order to meet the requirement of the fly-by-light computer system, the overallstructure of a modular, opening fly-by-light system is proposed for realization. Then the signal input/output processing backboard and high-speed MIL-STD-1773data bus backboard are developed. Thetest results of the principle prototype show that the fly-by-light control computer has characteristicssuch as light weight, small volume, high data transmission rate, good reliability, simple structure andeasy realization, so it can be directly apllied to the engineering of the next generation military andcivil aircrafts.Thirdly, a fly-by-light/power-by-wire actuator is established according to the actual situation, andthe key hardwares, mathmatical model of the DC motor and the PI control law with double loops isdeveloped. The dynamic and static characters of the actuator show that it has advantages of lightweight, small volume, Large output torque, fast dynamic response, high control precision and stronganti-interference ability, and is very suitable for engineering application.Fourthly, In order to adapt to the requirement of the fly-by-light system of carrier based aircraft, anadaptive control law based on fuzzy parameters tuning and model following is designed after thenonlinear aerodynamic model of the F/A-18aircraft is established and analysed. And the controlprinciple and design method are given. Then the visial landing verification system based on fly-by-light is established. The test results of this system show that it has good dynamic and staticprecision, real-time and adaptivity verified by the visial landing control system.Finally, a basic structure of triple redundancy flight control system is gived to improve thereliability and fault tolerace. An optical cross-channel data link with fault-tolerant capability isproposed, and the principle prototype is established. Then the reliability model of the opticalcross-channel data link is analyzed and simulated, and the simulation results show that it has multiplefault working ability, and has the advantages of simple structure, easy maintenance and good workingstability. The3D visualization platform for triple redundancy integrated flight/fire control system isestablished, and provided a general technique development platform for the fly-by-light system.