Design And Implementation Of Control System Of Turn Window Mechanism In Wind Tunnel Half-model Test

Wind tunnel test of the modern transport aircraft,span length,larger shrinkage model,has serious scaling effects for its span length and larger shrinkage model.The wind tunnel only makes whole model test about 1:50,so that Reynolds model test than when flying low Reynolds number is an order of magnitude or more.Most modern aircrafts use advanced supercritical wing,and the supercritical wing is very sensitive to the Reynolds number.Therefore,in order to improve the test Reynolds number,the half-model test section is had to be built.Combined with the overall function requirement of the model attitude control in the half-model test section,the characteristics of control system of half-model turn window mechanism and a line support mechanism is analyzed in detail.The data communication between PLC and the host computer is designed based on Mitsubishi Q series PLC.At the same time,a set of control software with convenient operation and friendly interface are developed.When the attack angle is controlled by a line supporting mechanism,the turn window mechanism both sides of a wall must be run in synchronism,because of large stress model.At first,the synchronization control strategy of the line support mechanism system is studied,then the synchronous control flow of line of support system is design.Finally,the control algorithm of integral separation is selected to realize synchronous operation on both sides of the turn window.Meantime,the multiple protective measures is taken,in order to ensure the safety of equipment.This system has been used in model wind tunnel test,and has practical value to verify the flight characteristics of modern transport.The realization of the synchronous control of line supporting mechanism,builds a good platform for the following research and the design of similar wind tunnel control system.