Development Of Missile Virtual Flight Semi-physical Simulation And Control System For 2m Supersonic Wind Tunnel

A virtual flight semi-physical simulation control system of missile for 2m supersonic wind tunnel is designed in this dissertation.It constitutes a missile wind tunnel test system with the model support device together.An important guarantee is provided for studying the missile’s motion characteristics and aerodynamic characteristics comprehensively during flight by the system with integrating instruction receiving and controlling,data acquisition and processing,data analysis and display.Firstly,the overall scheme design of data acquisition and control system in missile semi-physical simulation is proposed according to the system performance and technical requirements after analyzing and demonstrating the feasibility of the design of the wind tunnel virtual flight test system.A hardware system is built based on an industrial control computer and a PXI expansion chassis.High-performance measurement and control boards are used to implement data acquisition and communication.The solution of Windows 7 + RTX64 is applyed for software platform.The friendly interface design of human-computer interaction is realized by making full use of the GUI resources of Windows under the premise of ensuring real-time performance.The development cycle is shorten,the development costs is reduced effectively and the performance of real-time and the high precision of the control are ensured by adopting the overall scheme design.Then,the selection and design of hardware for flight simulation console,dynamics simulation computing platform and power module are discussed.The performance of industrial control computers,expansion chassis,program-controlled power supplies,and various measurement and control boards are analyzed specifically.The physical connections and communication methods between the modules are designed.Next,the basic flow of developing real-time drivers for the PXI bus measurement and control board under RTX64 is explained in detail.The communication method is designed between the RTSS process,the Windows process linking Rt Api real-time library and the ordinary Windows non-real-time process in order to achieve data acquisition,processing and display in real time.Aiming at the control requirements of the model in the wind tunnel virtual flight test,three execution modes of the rudder are briefly analyzed.According to the actual needs,the design of the main control software,power monitoring software,curve display software and data playback software are completed.Finally,the test results and analysis of the system are given.Each module of the system works normally,and the sensor data such as balance,gyroscope,and encoder can be collected synchronously in real time according to the working timing of the missile.The deflection of the rudder can be controlled correctly for different flight modes;the correctness of the control algorithm is proved through analyzing the data saved in the test.