Research On Automatic Flight Control Simulation Of Distributed Maintenance System

The distributed maintenance system is a virtual training platform for civil aircraft maintenance.At present,most of the training tasks on the distributed maintenance system are based on the ground scene.The lack of the flight part has certain limitations,so it is necessary to expand the basic functions of the flight process.When designing the basic functions of the flight process,automatic flight control simulation is the key component,this article will focus on this research.When simulating the automatic flight control law of a specified model,the data package information provided by the original company of the model needs to be referenced,but it is not easy to obtain.To this end,this paper adopts a simulation strategy based on data optimization of Quick Access Recorder(QAR),in order to improve the simulation degree of the designated aircraft flight control law when there is no data packet.Based on the realization of flight simulation,a functional model of the system fault effects during flight is established to achieve training purposes such as setting faults and observing fault effects during flight.The content of this article is as follows:First,based on the distributed maintenance system,the six-layer structure of the flight module was designed,including the human-computer interaction layer,the logical solution layer,the flight order layer,the control law layer,the aircraft model layer,and the status display layer.Combined with the design requirements of the aircraft model layer,the feasibility of Ftop for distributed maintenance system flight simulation was analyzed,and the general dynamic model in the Ftop was instantiated according to the characteristics of A320 model.Secondly,a variable universe fuzzy PID control method based on QAR data optimization is proposed.And this method is used to simulate the longitudinal control law,lateral control law and airspeed control law of A320 aircraft in the climb,cruise and descent stages.During the design process,the corresponding QAR data is selected and pre-processed according to each controlled flight state parameter at first.The selected data is re-sampled to make it consistent with the parameter output frequency of the simulation loop to effectively obtain the deviation of the two in the same state.Then the objective function is constructed with this deviation,and the flexible factor in the process of adjusting universe is optimized through the differential evolution and levy biogeography based optimization(DELBBO),so as to finally improve the simulation degree of the designated aircraft model flight control law.Then,the automatic switching logic between flight modes is established at the flight order layer,and the functional model of the system fault effect during flight is established at the logic solution layer.Finally,the script file of automatic flight control is created in the control law layer,and the communication mechanism in the flight module is established using two transmission protocols of TCP and UDP,and finally a distributed maintenance system with real-time flight simulation function is built.Based on the distributed maintenance system at this time,the flight experiment is carried out.The experimental results show that the control law designed in this paper has a good simulation effect,and the fault effects function model established is also effective.