The Design And Implementation Of Flight Control System Test Flatform Based On Virtual Technic

Unmanned Aerial Vehicle(UAV) is a complex system. As UAV is unmanned, the flight control system of UAV?s high reliability and stability is required. The development, debugging and validation of the software for the flight control system mostly depends on the real flight control computer platform, and the closed-loop experiment for the flight control system also need specific hardware platform to complete. But the flight control computer has the trait of a long development cycle and high complex and heavy workload, let the hardware which has software can?t do the real software test, software and hardware syntheses, system level syntheses, closed-loop test before the hardware delivery. This let the software for the flight control system will be restricted by the flight control computer?s development, the development and validation of flight control code can?t be carried out in parallel. Eventually, this led to the flight control system software?s development efficiency be lower and development costs more.For solving the above problems and avoiding the disadvantage that flight control softwares can?t be decelopmented and tested concurrently without physical validation platform,this paper carries out the design and implementation of a virtual test flatform whose function and structure with the real flight control test flatform on the Simics virtualization simulation platform.Thereform,the dissertation has highly engineering practical value.The main work of the task content:(1) according to some model of the real flight control computer, the demand of virtual flight control computer and integtated test facility(ITF) are analyzed.(2) according to the design requirements of the real flight control computer to finisn the design of the virtial flight control computer,include redundancy management and CPU board model.(3)finish the CPU board model,it includes the transplanted MPC755 core model,the built of storge model, EPIC model, Timers model,disperse interface model and watchdog model.(4)according to the demand of flight control computer?s peripheral equipment, 659 bus model, SIO board model, DIO board model,AIO board model and mother board model are built. Finally,according to the demand of ITF,finish the desgin and implementation of ITF. and the whole virtual flight control system is realized.The advantage of virtual flight control computer is that the flight control system developers can test the flight control software on PC.With the reverse of same theory the virtual flight control system platform can be tested.The virtual flight control system owns self preponderance that the real physical validation platform not.It can realize that the development and test of virtual flight computer request the restriction of real physical validation platform, increasing the efficiency and reducing the cost of developing software.Besides,virtual flight control computer could simulate flight control system software without real physical platform,and raise detail demand of design and built of real physical platform.