CAJ | 학술논문

在某型迫击炮无控弹结构基础上，将其引信改为固定鸭舵修正引信，采取直接利用原有尾翼结构、加大翼片面积和减少翼片数量三种尾翼设计形式，分别构建3个弹体模型，运用CFD计算软件对3种弹体模型的阻力系数、升力系数、俯仰力矩系数变化规律进行仿真，得到具有一定修正能力且满足全弹道飞行稳定性要求的弹体模型方案，其仿真结论可为尾翼稳定迫击炮二维弹道修正弹的研究提供参考。
재모형박격포무공탄결구기출상，장기인신개위고정압타수정인신，채취직접이용원유미익결구、가대익편면적화감소익편수량삼충미익설계형식，분별구건3개탄체모형，운용CFD계산연건대3충탄체모형적조력계수、승력계수、부앙력구계수변화규률진행방진，득도구유일정수정능력차만족전탄도비행은정성요구적탄체모형방안，기방진결론가위미익은정박격포이유탄도수정탄적연구제공삼고。
Based on the uncontrolled mortar projectile, this paper changes its fuse into canard correction fuse, using three forms as using original fins, increasing fins area and decreasing fins amount to build three simulation models. By using CFD software it generates meshes of each model, it simulates the changing laws of coefficient of drag, coefficient of lift and pitch?ing moment coefficient, gets a projectile scheme that satisfies requirement of correction and flight stability, the conclusion provides aerodynamic reference for future research.