CAJ | 학술논문

为了研究飞行环境下导弹折叠弹翼的展开过程，文中介绍了如何采用气动分析软件CFD-FASTRAN对其进行模拟，包括问题描述、网格划分、计算参数设置等。根据计算结果分析给出了导弹4片弹翼展开过程中的同步性、展开角速度情况以及弹体姿态和姿态角速度的变化情况等。结果表明，模拟方法可行，模拟结果可为导弹总体设计、弹道设计及弹翼机构设计等提供参考依据。
위료연구비행배경하도탄절첩탄익적전개과정，문중개소료여하채용기동분석연건CFD-FASTRAN대기진행모의，포괄문제묘술、망격화분、계산삼수설치등。근거계산결과분석급출료도탄4편탄익전개과정중적동보성、전개각속도정황이급탄체자태화자태각속도적변화정황등。결과표명，모의방법가행，모의결과가위도탄총체설계、탄도설계급탄익궤구설계등제공삼고의거。
In order to study the deployment process of missile folded wings in flying environment, The CFD software CFD-FASTRAN was used for simulating it, including problem description, mesh generation and calculation parameter setup etc. According to calculation result, the synchronization and angular velocity of four folded wings as well as missile attitude and angular velocity during deployment process were given. The results show that the simulation method is feasible, the calculation result could offer reference basis for the missile about overall design, trajectory design and wing structural design etc.