Design Of Wireless Data Acquisition System For Aircraft Load

Aircraft are widely used in civil and military fields as a common means of transportation.This requires that the aircraft should have sufficient margin of structural strength in the design process to ensure that the actual load of the aircraft meets requirements of structural strength for design under extreme conditions such as harsh atmospheric environment and different flight postures.Aircraft load test aims to obtain the condition of actual load of aircraft and provide the basis for the structural strength design of aircraft.Insufficient design load will lead to potential safety hazards in actual flight.On the contrary,excessive design load will affect maneuverability of aircraft and increase the cost of manufacture.So aircraft load test is very important for design and manufacture of aircraft.The purpose of aircraft load test is to obtain the load distribution of main structural components of aircraft.At present,the common method of measurement is to distribute sensors on measured points.By obtaining the structural deformation of the aircraft and calculating the mathematical relationship with the load,the actual load of aircraft can be obtained by using the mathernatical relationship.Because a large number of measured points need to be laid on structural components of aircraft during the test,it will increase the test cost to lay a large number of cables.In order to solve the above problems,this thesis designs a wireless data acquisition system based on ZigBee,and designs the corresponding wireless node of strain measurement based on strain method.Considering the influence of ambient temperature on load measurement a temperature measurement wireless node is designed to compensate the strain data at measured points.In order to meet requirements of a large number of data measurement,this thesis designs a host node according to the characteristics of Zi gBee network to realize the control and data transmission functions of each measurement node.In order to facilitate the data processing and managenent,this thesis also designs the PC software for reception,storage,display and export of data.These data can be used as original data for the establishment of load equation.After testing,the key functions of the wireless data acquisition system for aircraft load designed in this thesis can run stably,including data transmission function,data storage function,strain measurement function,temperature measurement function and multi channel measurement function.The system can not only greatly improve the efficiency of cable layout and reliability in aircraft load test,but also reduce the interference of long-distance transmission of sensor measurement signal.This method has a good reference for other occasions of multi-measurement points.