Research On The Integrated Control Of Electro-mechanical System For Civil Aircrafts

The integrated control of airborne electro-mechanical systems is theoretically researched at the top system level in this thesis, and the multi-system airborne integrated control and management strategy is explore as well. I have a priority on architecture of integrated electro-mechanical system (IEMS), control law design of electro-mechanical subsystem (Environment Control System, Landing Gear System, and Hydraulic System). Based on the above theory, the paper discusses the design plan and development on IEMS verification platform.In the research on the architecture of IEMS, This paper analyzes decisive element which initially determine civil aircraft architecture. Meanwhile, It explains the advantage of the design plan and optimize the system structure.In the research on control law of electro-mechanical system, The paper respectively analyzes on the objects of Environment Control System, Landing Gear System, and Hydraulic System and build the mathematic and simulation model of cooling system,thermal loop temperature control,electronic cabin temperature control,cabin temperature control,cabin pressure control,anti-skid brake control,nose geer steering control,hydraulic pump pressure control. While in the control laws part, the integrated control laws are figured out through clear and improved integrated controlling method of electro-mechanical systems and through the analysis of signals of each system.In the design of IEMS verification platform, the hardware environment design is determined, function planning of each part described and system software design also determined. In the part of verification platform development, the thesis solves the communication issue of distributed computer system, designs each system interface, completes data exchange and finally verifies the results through simulation.The theoretic research in this thesis is an exploration towards integrated electro-mechanical control of civil aircrafts in China and has reference value for further physical realization and engineering application of IEMS in civil aircrafts.