空气动力学学报
空氣動力學學報
공기동역학학보
ACTA AERODYNAMICA SINICA
2014年
6期
861-867
,共7页
多场耦合%长时间气动加热%热环境%防热设计%高超声速飞行器
多場耦閤%長時間氣動加熱%熱環境%防熱設計%高超聲速飛行器
다장우합%장시간기동가열%열배경%방열설계%고초성속비행기
multi-field coupling%long-duration aeroheating%aerothermal environment%thermal protec-tion design%hypersonic vehicles
新一代高超声速飞行器的发展给防热设计问题带来严峻挑战。根据飞行器热环境多场耦合特性，提出了一种基于多场耦合的热环境数值分析策略，并在此基础上发展了基于 Navier-Stokes 方程的流场 CFD 分析程序，通过有效的界面数据传递算法，实现了与结构有限元热分析软件的耦合，形成了基于流场与结构耦合传热的飞行器热环境多场耦合数值分析方法。以典型圆管前缘为计算模型进行了程序验证，并对稳态和非稳态飞行环境下的流场与结构耦合传热特征和规律进行了数值分析研究。结果分析表明，该方法能够有效地刻画流场与结构之间的耦合传热特征和规律，预测和分析飞行器热环境的空间和时间分布特性，从而可为防热设计的选材和优化提供可靠的参考依据和分析手段。
新一代高超聲速飛行器的髮展給防熱設計問題帶來嚴峻挑戰。根據飛行器熱環境多場耦閤特性，提齣瞭一種基于多場耦閤的熱環境數值分析策略，併在此基礎上髮展瞭基于 Navier-Stokes 方程的流場 CFD 分析程序，通過有效的界麵數據傳遞算法，實現瞭與結構有限元熱分析軟件的耦閤，形成瞭基于流場與結構耦閤傳熱的飛行器熱環境多場耦閤數值分析方法。以典型圓管前緣為計算模型進行瞭程序驗證，併對穩態和非穩態飛行環境下的流場與結構耦閤傳熱特徵和規律進行瞭數值分析研究。結果分析錶明，該方法能夠有效地刻畫流場與結構之間的耦閤傳熱特徵和規律，預測和分析飛行器熱環境的空間和時間分佈特性，從而可為防熱設計的選材和優化提供可靠的參攷依據和分析手段。
신일대고초성속비행기적발전급방열설계문제대래엄준도전。근거비행기열배경다장우합특성，제출료일충기우다장우합적열배경수치분석책략，병재차기출상발전료기우 Navier-Stokes 방정적류장 CFD 분석정서，통과유효적계면수거전체산법，실현료여결구유한원열분석연건적우합，형성료기우류장여결구우합전열적비행기열배경다장우합수치분석방법。이전형원관전연위계산모형진행료정서험증，병대은태화비은태비행배경하적류장여결구우합전열특정화규률진행료수치분석연구。결과분석표명，해방법능구유효지각화류장여결구지간적우합전열특정화규률，예측화분석비행기열배경적공간화시간분포특성，종이가위방열설계적선재화우화제공가고적삼고의거화분석수단。
The development of new-generation hypersonic vehicles presents a major challenge in the de-sign of thermal protection systems.Sustained hypersonic flight within the atmosphere can result in severe aerodynamic heating phenomena.It is a physical fact that significant interaction occurs between the external aerodynamic heating and the structural heat transfer within the vehicles.Through analyzing the multi-field coupling characteristics of aerothermal environment of hypersonic vehicles,a multi-field coupling numerical analysis approach for predicting aerothermal environment is proposed in this paper.This approach couples the computational fluid dynamics (CFD)codes based on the Navier-Stokes equations with the general com-mercial finite element method (FEM)software by the reliable interfacial data exchange method.Considering a cylindrical leading edge as test case,the fluid-structural thermal coupling characteristics along the steady and unsteady flight trajectory is numerically investigated.It is indicated that the proposed approach could ac-curately predict the fluid-structural thermal coupling characteristics,and achieve the analysis of spatial and temporal distribution characteristics of aerothermal environment,thus providing the reliable analysis tool for the material selection and optimization in the design of thermal protection systems.
