The Design Of Measurement And Control System Of Inlet Experiment In Low Speed Wind Tunnel

For any use of aircraft or aero-engine missile,the inlet is a very important component.In the development of a new inlet,in addition to a lot of calculation aerodynamic theory,we also need to do a large numbers of scale model wind tunnel tests.Based on the FL-8 specific wind tunnel experiment situation,based on current measurement and control in the field of new technologies,designed a more advanced inlet current monitoring system.The system includes steady-state measurement system,dynamic measurement system,flux and pressure control the three main nodes.In this paper,which sets the overall design programme of the measurement and control system,and discussed in detail the three major component nodes.Because the technology of steady measurement are more mature,we only introduce it simply,We focus on companies the dynamic measurement technology based on Odyssey of Necolet Inc and the use of the AC servo control system of pressure flux control methods.Give some diagrams of the hardware and principle of two parts.In software design,using a common modular design rules,Isolate a number of modules from the software according to actual needs,during the test may be necessary to make calls.Each module is independent in functional,and through the standard data interface establish the organic links.Of all the modules,we focus on the pressure flux control module.The module used fuzzy PID contrr'strategy,give the specific algorithms and software flow charts and comparison results of simulation.The current measurement and control system has been successfully applied on FL-8 wind tunnel tests,Test results show that the system operating normally reliable,with high accuracy in dynamic and stability,it is very good to meet the test requirements,performance of the test system is meet to the Design indicators.