| Airbag cushioning technology is commonly used in engineering, aviation,aerospace and defense industry. It can obviously reduce the landing impact load of theimportant instruments and equipments. With the advantages of portable structure,high efficiency and wide adaptation, it is suitable for the application of the Marslanding system.Subject to the complicated structure and high reliability requirements of theairbag-lander and the extreme working conditions during the Mars landing, its designand analysis often involve physical fields and large-scale scientific computing. Itscomputing "efficiency" and "precision" have become bottleneck problems in this area.It is significant for the Mars exploration projects and the design and research of theequipment to solve the bottleneck problem and optimize the design of the landerbased on the Super Calculate Platform and to conduct typical demonstrations aimed atthe national major projects.Based on the Super Calculate Platform and the technology of CAE numericalsimulation analysis, this thesis studies the cushioning performance of the airbagcushioning system for Mars landing through the combination of the finite elementsimulation and experimental validation. The main work includes:(1) Putting forward an overall design of the airbag lander based on the functionalrequirements and technical indicators of all types of equipment as well as theadvantages and disadvantages of existing domestic and overseas landers, andcompleting the production, processing and assembly of the physical model;(2) Based on the actual working conditions and the functional requirements ofthe airbag cushioning system for Mars landing as well as the simulation calculationresults of the finite element model and tests needed, putting forward the overalldesign scheme of Mars landing test-bed, and completing the structure design and thetest bench of strength, stiffness and reliability of the main components;(3) By the finite element analysis software, establishing the finite elementmodels of the airbag cushioning system for Mars landing, submitting them to thesuper calculate platform and getting the corresponding finite element simulationanalysis data; (4) Conducting the Mars airbag lander buffing test, comparing the experimentaldata and simulation data and finding the simulation calculation results match the testresults well, which verify the validity of the finite element model;(5) Taking the initial parameters of Mars lander airbag system as the object,sampling different parameter values in a certain interval to reconstruct the model,conducting the Mars landing system simulation based on the Super Calculate Platform,applying genetic algorithm to optimize the initial parameters, getting a reasonableinitial parameters of the Mars lander airbag system and making the airbag bufferachieving optimal performance. |
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