Design Of Data Acquisition System In Aeroengine Test-run And Simulation Of Vectoring Thrust Nozzle

The thesis presents the design and realization of the data acquisition system for aeroengine test-run. Considering the current domestic and foreign development of the testing system technology,as well as, the users'demands, a detailed design scheme of the system for aeroengine test-run with the virtual instrument technology and PXI bus technology is proposed. The design and programming of the system's software and the debugging of the system have been done with the PXI modules and SCXI modules of the NI Company. The testing shows that the data acquisition system for aeroengine test-run with the virtual instrument technology not only has good real time, high reliability and nice expansibility ,but also can shorten the development cycle and cut the development costs. All these facts indicate that the system has good economic benefits. This thesis not only provides information for the design and realization of the similar data acquisition system but is also an attempt and realization of the virtual instrument in the domestic aero testing field.The thesis simultaneously works on the modeling and simulation of the aeroengine vectoring thrust nozzle's dynamic system. The actuating cylinder displacement through some servovalve's control causes the change and deflection of the axisymmetric vectoring thrust nozzle's throat area A8 and the nozzle area A9, the motion mechanism of which is quite complex. The geometrical relation,kinematical and dynamic model of the axial-symmetric vectoring thrust nozzle are established, through which we can simulate the steady and dynamic calculation of the cylinder displacement,the throat area,the nozzle area,the orientation and angle of deflection.