Design And Development Of The Mach Control System For Continuous Transonic Wind Tunnel

With the rapid development of aerospace science and technology,wind tunnel has become the most widely used tool in aerodynamics research field.It can be through the relevant test technology to verify the aerodynamic layout of the aircraft and to assess its aerodynamic performance for the development of our model aircraft or air weapons and equipment to make outstanding contributions.Our new construction of continuous transonic wind tunnel is one of the best quality of the domestic flow field of 0.6 meters wind tunnel.It is mainly used in routine experimental research,aerodynamics basic application research,icing technology research,etc.But also for our research institute will be the construction of a greater degree of continuous wind tunnel for guidance,to study and verify and solve the more large-scale continuous wind tunnel laid the foundation for the key technology.In order to make the new construction of 0.6 meters continuous transonic wind tunnel to play its due function,the need to design and develop advanced control system.Mach control system is the core part of the wind tunnel control system,but also the key part of the normal operation of other subsystems.In this thesis,the purpose,significance and task of the research on the realization of the Mach number control system of 0.6 meters continuous transonic wind tunnel are expounded.As the Mach control system belongs to the core part of the wind tunnel control system,this thesis introduces the design requirements of the 0.6 meters wind tunnel and the overall design of the relevant control system.Secondly,the main factors influencing the Mach number are analyzed,and the difficulties and key techniques of the Mach number control system of continuous wind tunnel are summarized.Then the control strategy and method of Mach number are discussed in detail.Combining PID control theory and feedforward control theory,the Mach control system based on main compressor,two-throat and auxiliary compressor is designed respectively.And the hardware design of the control system based on PXI controller is completed.Finally,the modular design idea is used to study the software design of Mach number control system.The software architecture and process are designed and programmed in LabVIEW graphical language,and the man-machine interface is realized,so it is very good to complete the 0.6 meters continuous transonic wind tunnel Mach control system development.In this thesis,the design and development of the 0.6 meters continuous wind tunnel Mach control system,respectively,after hardware debugging,software debugging,hardware and software joint,through the key technology research and solution,the design and development of the Mach number control system with 0.6 meters continuous transonic wind tunnel is completed.The actual application of the wind tunnel shows that the master control system has reached the design requirements,high degree of automation,friendly and friendly interface,flexible and convenient to use,the test data show that all meet the national military standard technical requirements,to achieve the expected aims.The wind tunnel is now put into practical use of the project,the operation effect is good.