Study On Hypersonic Vehicle Fluid-thermal-structure Multi-physics Coupling Calculation

Hypersonic aircraft have rapid global strike capability, superior penetrationcapability and other obvious military strategic advantages, it has become an importantdirection of aerospace development in today’s century. Hypersonic aircraft generateaerodynamic heating and heat transfer problems during flight, this problem is amulti-physics coupling problem which includes flow field, temperature field and thestructural field. In the numerical simulation, the coupling calculation method must beused in order to accurately estimate the temperature and thermal deformation of aircraftstructure in hypersonic environment, then for the thermal protection system design andstructural design work to do important reference.This article used loose coupling calculation method, using MPCCI joint FLUENTand ABAQUS software, achieved the flow-heat-structure Coupling problem ofhypersonic vehicles. Among them, the wall heat flux and the wall temperature ofFLUENT and ABAQUS were extracted useing MPCCI to exchange and transfer, in thisway, we achieve the cross-iteration two-way coupling calculation between the twosoftwares.Firstly, the problem of the classic tube spoiler was simulated. The shock positionand shape calculated using this method are both consistent with the experimental resultsof the model, the pipe internal temperature distribution are also consistent with theforeign literature calculation results, this verify the validity of our method. In addition,we made a detailed analysis to the tempreture, thermal stress and strain, deformation ofthe tube structure at different times.Based on the above study, around the head structure design of the actualhypersonic vehicle, we had researched the protective performance with different headball radius or different thermal protection materials. And through the simulation we hadreasearched the temperature and deformation of the structure of the hypersonic vehiclein extreme conditions, calculation results show that the aircraft thermal protectionmaterials and structural design had meted mission requirements.Our method of calculating for the hypersonic vehicles flow-thermal-structurecoupling problems was actually running in good condition, high the computationalefficiency is high, the calculation results have high reliability, it has a certain value inengineering applications.