CAJ | 학술논문

气动加热造成的结构温升可能造成飞行器结构失效从而带来安全隐患。准确预测结构温度场在高超声速飞行器热防护系统与结构设计中显得尤为重要。气动热与传热耦合是提高结构温度场预测精度的有效手段，经长期研究与发展，不管是耦合方法研究还是实际工程应用都已开展了大量工作。但这些研究工作均未考虑结构变形对气动加热和结构温度场的影响。而在实际飞行过程中，特别是长时间飞行后，结构变形对结构温度场的影响往往是不能忽略的，对气动力／热环境也都有直接的影响。本文以飞行器静热气动弹性计算方法为基础，对高超声速飞行器机翼模型进行了考虑热气动弹性变形影响的气动热与传热耦合计算，并与不考虑变形对热环境影响情况的计算结果进行了对比分析。结果表明，虽然对于大面积区域变形对气动热／结构温度场的影响较小，但对于热防护结构重点关注且精度要求较高的前缘驻点附近区域计算结果变化明显。由此，也说明了考虑弹性变形对结构温度场预测的重要性。该研究工作为进一步提高飞行器结构温度场预测精度和结构热安全性能评估能力奠定了基础。
기동가열조성적결구온승가능조성비행기결구실효종이대래안전은환。준학예측결구온도장재고초성속비행기열방호계통여결구설계중현득우위중요。기동열여전열우합시제고결구온도장예측정도적유효수단，경장기연구여발전，불관시우합방법연구환시실제공정응용도이개전료대량공작。단저사연구공작균미고필결구변형대기동가열화결구온도장적영향。이재실제비행과정중，특별시장시간비행후，결구변형대결구온도장적영향왕왕시불능홀략적，대기동력／열배경야도유직접적영향。본문이비행기정열기동탄성계산방법위기출，대고초성속비행기궤익모형진행료고필열기동탄성변형영향적기동열여전열우합계산，병여불고필변형대열배경영향정황적계산결과진행료대비분석。결과표명，수연대우대면적구역변형대기동열／결구온도장적영향교소，단대우열방호결구중점관주차정도요구교고적전연주점부근구역계산결과변화명현。유차，야설명료고필탄성변형대결구온도장예측적중요성。해연구공작위진일보제고비행기결구온도장예측정도화결구열안전성능평고능력전정료기출。
Thermal destruction of aircraft structure caused by aerodynamic heating is one of the hidden troubles to the vehicle safety.To predict the structure temperature field of hypersonic vehicle accurately is very important for the thermal protection system design.Coupling methods of aerodynamic heating and heat transfer,and corresponding engineering applications have been carried out in a lot of works worldwide up to date.However,the influence of structural deforma-tion on aerodynamic heating and structural temperature field was generally ignored in many of these studies.In an actual flight,especially after a long-time flight,the structural deformation caused by the coactions of aerodynamic and temperature rise has some direct impact on the aero-dynamic heating and structural temperature field,and needed to be taken into account.In this paper,coupling effects of aerodynamic heating and heat transfer on a hypersonic aircraft wing model were investigated considering the influence of aerothermoelasticity deformation based on static aerothermoelasticity analysis method.The results show that,for the great mass of region, deformation of thermal structure has inconspicuous effect on temperature field,structural stress and strain.Nevertheless,for the region near to the stagnation point and leading edge,where the key regions of thermal protection system design,the calculation results change obviously.Therefore,during the solution process concerning aerodynamic and structural thermal coupling effect,the decoupling method can be considered to reduce the calculation cost when aeroelastic deformation is small.The present work lays the foundation for improving the prediction accuracy of the tem-perature field of aircraft structures and structural performance evaluation capacity.