Design Of Dynamic Multiphysics Test System

Icing seriously affects the flight safety of the aircraft.The most susceptible parts of the aircraft are the main wings,the horizontal tail,the engine air intake,the atmospheric data sensor,and the windshield.Generally speaking,the main structure of the aircraft to generate lift is the wing.After icing,the shape and flatness of the wing change slightly,and the layout of the aerodynamic structure inside the wing will also change,which in turn causes the lift coefficient and drag of the aircraft wing If the ratio drops,the aircraft's takeoff and landing performance will decrease.The main reason for the formation of ice on the surface of the aircraft is that under the meteorological environment conditions with high content of cold water droplets and low temperature,the cold water droplets in the atmosphere collide with the metal surface of the aircraft to form ice.The wing will freeze,which will not only increase the weight of the aircraft,but also cause serious damage to the flight safety of the aircraft if key components freeze.This paper is to build a simulation experiment platform for wing icing and deicing to simulate the icing phenomenon that occurs during the actual flight of the aircraft.By using the electric pulse deicing experimental method,the researchers can derive the influencing factors of the deicing effect.According to the characteristics of wing de-icing,this paper designs a dynamic multiphysics test system for simulation.The coil is fixed on one end of the cantilever of the lifting platform.The lifting platform is controlled by the PLC to control the servo motor to drive the screw to rotate coaxially and adjust the height of the lifting platform.The pulse signal acts on the coil,the electric pulse signal is sent by the high-voltage pulse power supply,the voltage and pulse width of the electric pulse can be adjusted,an electric field will be generated around the coil,and the electric field will induce a magnetic field around the wing skin,so that the coil and the wing Pulse force is generated between the skins.This pulse force will cause the skin to have high acceleration and small amplitude vibration.The ice layer will be quickly shattered in a short time to achieve the effect of deicing.Controlled by NI 8840 Device,NI 1840 chassis and acquisition card to collect data of laser displacement sensor,eddy current sensor,magnetic field sensor,force sensor and torque sensor around the skin,and then process,analyze,query and display the data by Labview host computer software can test various parameters.This paper mainly introduces the construction of the entire simulation system,including circuit design,mechanical structure design,hardware selection,upper computer software design,lower computer software design,etc.The experimental part needs further exploration by researchers.The design of this paper plays a very important role in studying the effect of wing de-icing.