Design And Fatigue Analysis Of Split Flying Vehicle Docking System

Aiming at the increasingly severe urban traffic congestion problem,split flying vehicle has been proposed as a new mode of transportation.It can form two traffic modes suitable for road surface and air through docking of different combinations between modules.Compared with the traditional integrated flying car,it has the characteristics of small size and low load while expanding the urban traffic dimension.The components of the split flying vehicle are air module,passenger capsule and ground module.In order to realize flexible and stable docking among the three modules,the autonomous docking system,as one of the key technologies,is particularly important.In view of the lack of relevant studies at present,a new type of split docking system for flying vehicle was proposed based on the evaluation of the research status of docking systems in various fields at home and abroad,and the overall structure and electromechanical system were designed.The simulation and verification were carried out according to the relevant performance indexes of the docking system,and then the fatigue life of the structure was predicted by means of finite element analysis.Finally,a prototype experimental platform was built to verify the rationale of the split-type docking system.First of all,based on the analysis of the modal transition and operating conditions of the split flying vehicle in driving state,combined with the overall project requirements,the working mode and structure of the docking system were designed,the guidance and locking schemes of the upper and lower docking systems were determined,and the structure was designed by threedimensional modeling software.At the same time combined with the analysis conditions of the autonomous electromechanical control system design,determine the electromechanical control flow and communication system scheme.Secondly,in order to verify that the docking system design meets the performance indexes,algebraic tolerance analysis is carried out on the guidance capture domain,and the acquisition range of the docking system meets the requirements under the specified pose deviation.The dynamics simulation analysis of the docking system under different working conditions was carried out by ADAMS,and the simulation analysis of the load history under the driving state was carried out.Then the finite element simulation of the key component of the docking system are carried out to verify that its strength meets the index requirements under the ultimate working conditions.Then,the fatigue life of the docking system is predicted according to various working conditions.With ANSYS n Code Design Life combined with the load history obtained before,load mapping was carried out through the finite element analysis results,combined with the SN curve of the material and based on the nominal stress method,the damage life cloud map of the key components was obtained,and the life duration of nodes with less life in each area was calculated,which met the design requirements.Finally,according to the workflow of the docking system of split flying vehicle,a 50 kg scale prototype test platform was built,including the prototype framework of each module and the scale prototype of the docking structure.At the same time,the development board of the autonomous control system was built based on embedded development,as well as the display control interface of the ground station related to the communication system,and the locking experiment of docking system and the whole process docking experiment were carried out.It is verified that the docking system realize the requirements of overall guidance docking and locking.